Turbine blade with auxiliary guide plate

Abstract

A fluid flow turbine blade assembly for a turbine rotor includes a blade and a deflector extending in a span direction along at least a portion of the blade. At least a portion of an upstream surface of the deflector has a concave shape in a chordwise direction along at least a portion of a span of the deflector such that at least a portion of a chord line between a leading edge and a trailing edge of the deflector is disposed outside a profile defined between the upstream surface and a downstream surface of the deflector. The deflector has a substantially uniform thickness or a chordwise varying thickness between the upstream surface and the downstream surface. The deflector varies fluid flow on the blade in order to increase the contribution of the blade to the global torque generated by the assembly such that the global torque of the assembly is greater than the global torque generated individually by the blade without the benefit of the deflector under the torque contribution of the deflector.

Description

[0001] Cross - reference to related applications

[0002] This application claims the benefit of the filing date of U.S. Provisional Patent Application No. 63 / 409,479, filed on September 23, 2022, under 35 U.S.C. § 119(e), the disclosure of which is incorporated herein by reference.

[0003] Field of disclosure

[0004] This disclosure relates to improvements in the performance of turbine blades for wind turbines and water turbines. Specifically, this disclosure relates to a turbine blade assembly including one or more flow deflectors that may be arranged as a single or multiple deflector assemblies fixedly linked or operably (adjustably) coupled to an associated turbine blade and configured to increase the volume of fluid flowing over the pressure side and suction side of the associated turbine blade and / or to alter the fluid flow and resulting pressure distribution adjacent to the surface. The upstream or pressure surface of the flow deflector includes a recess that begins at the trailing edge of the deflector and transitions to a convex or straight section that ends at the leading edge of the deflector. The flow deflector may have a uniform thickness or a variable thickness between its leading edge and trailing edge. Each flow deflector is arranged such that its leading edge is behind the leading edge of the associated turbine blade with respect to the direction of movement of the blade, and the trailing edge of at least a portion of the flow deflector may be positioned closer to the oncoming fluid flow (wind or water) than the trailing edge of the blade. One or more flow deflectors may be arranged on the pressure side, suction side, or both sides of each blade. One or more flow deflectors may span the entire length of the associated blade or any portion thereof.

[0005] Background

[0006] Wind and water turbine blade designs have remained relatively unchanged in the recent past, with only incremental performance improvements over the last several decades. As a result, the industry has resorted to making turbine blades larger to increase output. This has led to manufacturing, transportation, and installation issues for wind turbine blades each weighing over 40 tons, and in many cases, the blades take months to be transported from their manufacturing location to their installation location. It is not uncommon for the logistics of transporting a single 32-ton blade to require up to a year of planning. Additionally, in some cases, the logistics complexity of transporting such blades from the manufacturing point to the installation point can render a wind turbine project economically unfeasible. Further, despite significant research and design efforts, the turbine industry has achieved only incremental improvements in blade performance over the decades. As a result, manufacturers have resorted to designing and producing increasingly larger rotor diameters with taller towers, thereby exacerbating transportation, assembly, and public resistance to industrial-scale wind turbine installations. Water turbine blade designs have also been hampered by a lack of substantial performance improvements, thereby limiting the locations of economically viable projects that could otherwise be reliably powered by continuous water flow.

[0007] Overview

[0008] A simplified overview is presented below to enhance a basic understanding of certain aspects described herein. This overview is not an exhaustive review of the claimed subject matter. Its purpose is neither to identify key or critical elements of the claimed subject matter nor to describe its scope. The sole purpose of this overview is to present some concepts in a simplified form as a prelude to the more detailed description presented later.

[0009] Aspects of the present disclosure are embodied in a rotor that can be part of a wind-driven or water-driven turbine and includes a deflector that is positioned closer to an oncoming flow than the turbine blade to which it is attached and that deflects additional fluid flow over such turbine blade.

[0010] According to other aspects, the deflector can be configured for wind turbines, water turbines (including but not limited to hydrodynamic axial flow turbines) having different axial arrangements including, but not limited to, horizontal axes, inclined axes, and vertical axes.

[0011] According to other aspects, the deflector can be configured to span the entire length of an associated rotor blade, including the blade root.

[0012] According to other aspects, the deflector can be configured to affect the entire airfoil or hydrofoil portion of an associated wind or water rotor blade.

[0013] According to other aspects, the deflector can be configured to affect a portion of the airfoil or hydrofoil portion of a wind or water rotor blade.

[0014] According to other aspects, the flow deflector can be fixedly linked to the wind or water rotor blade.

[0015] According to other aspects, the flow deflector can be adjustably connected to the wind or water turbine blade, whereby the angle of attack of the flow deflector can vary.

[0016] According to other aspects, the flow deflector can include a leading edge, a trailing edge, a tip edge, and a root edge, each edge having a different geometric shape or a similar geometric shape.

[0017] According to other aspects, the shape of the perimeter of the flow deflector around its leading edge, tip end, trailing edge, and hub end can be generally quadrilateral or trapezoidal.

[0018] According to other aspects, the thickness of the flow deflector can be generally uniform.

[0019] According to other aspects, the flow deflector can have a varying thickness.

[0020] According to other aspects, the flow deflector can include an integral airfoil portion.

[0021] According to other aspects, the flow deflector can include an integral hydrofoil portion.

[0022] According to other aspects, the flow deflector can be twisted along its spanwise length.

[0023] According to other aspects, the flow deflector can have a rear concavity on the pressure surface and can have a corresponding convexity on the suction surface near its trailing edge.

[0024] According to other aspects, the geometry of the rear concavity (such as the radius of curvature and / or arc length) can vary from the tip end of the flow deflector to the hub end of the flow deflector.

[0025] According to other aspects, the flow deflector can have a front convexity on the pressure surface and can have a corresponding concavity on the suction surface near its leading edge.

[0026] According to other aspects, the flow deflector can have a front convexity near its leading edge.

[0027] According to other aspects, the flow deflector can have a reflected mean camber line.

[0028] According to other aspects, the geometry of the front convexity (such as the radius of curvature and / or arc length) can vary from the tip end of the flow deflector to the hub end of the flow deflector.

[0029] According to other aspects, the leading edge of the flow deflector can have a geometry that generally follows the trailing edge of the corresponding blade.

[0030] According to other aspects, the flow deflector can have a chord located outside the profile of the flow deflector.

[0031] In other aspects, the flow deflector may have a curved tip end.

[0032] In other aspects, the flow deflector may be positioned in the wake of the associated blade.

[0033] In other aspects, the flow deflector may be positioned such that its leading edge is behind the leading edge of the associated blade.

[0034] In other aspects, the flow deflector may be skewed such that the tip end of the flow deflector is closer to the respective blade and the hub end of the flow deflector is farther from the respective blade.

[0035] In other aspects, more than one flow deflector may be positioned closer to the flow than the respective blade.

[0036] In other aspects, the flow deflector may be positioned farther from the flow than the respective blade.

[0037] In other aspects, the flow deflector may have a fluid wall protruding from its pressure surface or suction surface.

[0038] In other aspects, the flow deflector may be composed of multiple segments that are mirror - manufactured as an integral structure of the flow deflector when assembled.

[0039] In other aspects, the flow deflector may be connected by a multi - component connector.

[0040] In other aspects, the flow deflector may have a fixed angle of attack.

[0041] By considering the following description and the appended claims in reference to the accompanying drawings, other features and characteristics of the subject matter of the present disclosure, as well as the operating methods and functions of the combinations of the related elements and parts of the structure and the economics of manufacture, will become more apparent, all of which form a part of this specification, wherein like reference numerals designate corresponding parts in the various figures.

[0042] Incorporation by reference

[0043] All publications, patents, and patent applications mentioned in this specification are hereby incorporated by reference herein to the same extent as if each individual publication, patent, or patent application were specifically and individually indicated to be incorporated by reference. Brief description of the drawings

[0045] The drawings incorporated herein and forming a part of the specification illustrate various embodiments of the subject matter of the present disclosure. In the drawings, like reference numerals represent the same or functionally similar elements.

[0046] Figure 1A is an isometric view of a three - blade wind turbine.

[0047] Figure 1B Is an isometric view of the cut side of a wind turbine nacelle, where the cut-away section shows the gearbox and generator.

[0048] Figure 2A Is a front isometric view of a wind turbine blade, which includes detailed views of the blade profile near the tip, center, and hub ends of the blade.

[0049] Figure 2B Is a rear isometric view of a wind turbine blade.

[0050] Figure 2C Is a cross-sectional view of a typical wind turbine blade near the hub end, revealing internal components.

[0051] Figure 2D Is a schematic cross-sectional view of a typical wind turbine blade, showing the relative airflow over the blade as well as lift and drag.

[0052] Figure 2E Is a cross-sectional view of a section of a typical wind turbine blade near the tip, showing beneficial areas on the pressure side and suction side of the blade.

[0053] Figure 2F Is a cross-sectional view of a section of a typical wind turbine blade near the hub end, showing beneficial areas on the pressure side and suction side of the blade, and an enlarged detail view of the trailing edge, which has a greater angle of attack and forms an additional beneficial area.

[0054] Figure 2G Is a schematic cross-sectional view of a section of a typical wind turbine blade, which shows the slope angles and types of forces on beneficial areas on the pressure side and suction side of the blade, as well as an enlarged detail view of the slope angle on the suction side.

[0055] Figure 3 Is an isometric view of a three-blade water turbine, where the cut-away section of the nacelle reveals the gearbox and generator assembly.

[0056] Figure 4A Is a front isometric view of a typical water turbine blade, which shows in detail the blade profile near the tip, center, and hub ends of the blade.

[0057] Figure 4B Is a rear isometric view of a water turbine blade.

[0058] Figure 5A Is a front view of a wind turbine, where the fairings are attached to the turbine blades and positioned to affect the entire airfoil section of each blade.

[0059] Figure 5BFront view of a rotor consisting of a deflector / vane assembly. The dashed lines depict the boundaries of the outer swept volume, the transitional swept volume, and the common swept volume. The enlarged side detail schematic exploded view depicts the volume relative to the oncoming fluid flow and the space between the regions. For clarity, the detail views are not drawn to scale and the vanes and deflectors are not shown within their respective three-dimensional spaces.

[0060] Figure 6 Front view of a wind turbine having a partial-span deflector coupled to a turbine blade and positioned to affect a portion of the airfoil section of each blade.

[0061] Figure 7 Front view of a water turbine having a deflector coupled to a turbine blade and positioned to affect the entire hydrofoil section of each blade.

[0062] Figure 8 Front view of a water turbine having a partial-span deflector coupled to a turbine blade and positioned to affect a portion of the hydrofoil section of each blade.

[0063] Fig.9A Front isometric view of a deflector, excluding any structure that attaches the deflector to the blade, where the cross-sectional views of (i) the tip end and the center section, (ii) the end view of the hub end, and (iii) the front cutaway detail view of the tip end are enlarged.

[0064] Fig. 9B Rear view of a deflector / vane assembly showing that the deflector leading-edge curvature matches the blade trailing-edge curvature, excluding any structure that attaches the deflector to the blade.

[0065] Fig. 9C Cross-sectional view of the tip end of an alternative embodiment of a deflector, with exaggerated camber to more easily show the geometry of the convex portion.

[0066] Fig.9D End view of the hub end of an alternative embodiment of a deflector, with exaggerated camber to more easily show the geometry of the convex portion.

[0067] Fig.9E Front view of a deflector / vane assembly, showing five detailed contour views starting from the tip end of the deflector and ending at the hub end of the deflector.

[0068] Fig.9F Side view of the deflector and blade profiles at the tip end of the deflector, showing the deflector angle of attack and its position relative to the blade.

[0069] Figure 9GA side view of the deflector and blade profile at 25% of the distance from the tip end of the deflector, showing the angle of attack of the deflector and its position relative to the blade.

[0070] Figure 9H A side view of the deflector and blade profile at the midpoint between the tip end and the hub end of the deflector, showing the angle of attack of the deflector and its position relative to the blade.

[0071] Fig.9I A side view of the deflector and blade profile at 25% of the distance from the hub end of the deflector, showing the angle of attack of the deflector and its position relative to the blade.

[0072] Figure 9J A side view of the deflector and blade profile at the hub end of the deflector, showing the angle of attack of the deflector and its position relative to the blade.

[0073] Figure 9K A rear view of an embodiment of the deflector / blade assembly, showing the fixed-link connector assembly and the associated rotational travel path around the rotor axis of rotation.

[0074] Figure 9L A rear cropped and enlarged view of the deflector / blade assembly and a single fixed-link connector assembly, showing an isometric view of enlarged details of the curved leading and trailing edges of the connector assembly working with the rotational flow.

[0075] Figure 9M A side view of the fixed deflector connector assembly including the deflector end flange, connector tube, and blade end flange, showing (i) a cross-sectional detail of the leading and trailing edges of the connector tube relative to the rotational flow, and (ii) an enlarged top cross-sectional detail of the leading and trailing edges of the connector tube relative to the deflector / blade assembly in the stationary position.

[0076] Figure 9N A cropped side view of the hub end of the deflector / blade assembly, showing a cross-sectional view revealing an embodiment of the connector assembly fixedly linked within the deflector and blade.

[0077] Fig. 10A A side view of the flow trajectory line impinging on the pressure surface of the blade in the absence of the deflector, with the blade in the stationary position and exposed to a wind speed of 2.0 m / s.

[0078] Fig. 10B A side view of the flow trajectory line impinging on the pressure surface of the blade and the deflector of the deflector / blade assembly, with the deflector / blade assembly in the stationary position and exposed to a wind speed of 2.0 m / s.

[0079] Fig. 10C Is Fig. 10ASide view of the pressure curves around the upstream and downstream surfaces of the blade.

[0080] Fig. 10D Is Fig. 10B Side view of the pressure curves around the upstream and downstream surfaces of the deflector / blade assembly.

[0081] Fig.10E Is Fig. 10A Enlarged side isometric view of a section of the blade, showing the surface pressures on the upstream and downstream surfaces of the section, and where the pressure regions are shown on the outer side of the upstream surface and the inner side of the downstream surface.

[0082] Fig.10F Is Fig. 10B Enlarged side isometric view of a section of the blade (the deflector is not shown in the figure), showing the surface pressures on the pressure surface and the suction surface of the section.

[0083] Fig.11A Is a side view of the apparent velocity flow trajectory lines around a section of the blade surface near the blade tip rotating in a 3.5 m / s wind without the benefit of a deflector.

[0084] Fig. 11B Is a side view of the apparent velocity flow trajectory lines around a section of the blade and deflector surfaces near the tip of the deflector / blade assembly rotating in a 3.5 m / s wind with the benefit of the deflector, including illustrative high-pressure and low-pressure regions.

[0085] Fig. 11C Is Fig.11A Side view of the pressure curves around the upstream and downstream surfaces of the blade.

[0086] Fig.11D Is Fig. 11B Side view of the pressure curves around the upstream and downstream surfaces of the deflector / blade assembly.

[0087] Fig.11E Is a front view of the upstream surface of the blade showing the pressure regions and associated fluid pressures in a 3.5 m / s wind without the benefit of a deflector, and an enlarged detailed cross-section of the blade near the tip end.

[0088] Fig.11F Is a front view of the upstream surface of the blade of the deflector / blade assembly (but where the deflector is not shown in the figure), showing the pressure regions and associated fluid pressures in a 3.5 m / s wind.

[0089] Fig.11GIs a rear view of the downstream surface of a blade showing the benefits of no flow deflector, showing the pressure regions and associated fluid pressures in a 3.5 m / s wind.

[0090] Fig.11H Is a rear view of the downstream surface of a blade of a flow deflector / blade assembly (but with the flow deflector not shown in the figure), showing the pressure regions and associated fluid pressures in a 3.5 m / s wind.

[0091] Fig.11I Is Fig.11E And Fig.11G Is an enlarged side isometric view of section "11I" of the blade, showing the surface pressures on the upstream and downstream surfaces of this section.

[0092] Fig.11J Is Fig.11F And Fig.11H Is an enlarged side isometric view of section "11J" of the blade (with the flow deflector not shown in the figure), showing the surface pressures on the pressure surface and suction surface of this section.

[0093] Fig. 12A Is a side view of the pressure curve around a section of the blade surface near the tip of a blade rotating in a 13 m / s wind without the benefits of a flow deflector.

[0094] Fig. 12B Is a side view of the pressure curve graph around a section of the blade and flow deflector surfaces near the tip of a flow deflector / blade assembly rotating in a 13 m / s wind with the benefits of a flow deflector.

[0095] Fig. 12C Is a front view of the upstream surface of a blade showing the benefits of no flow deflector, where the pressure regions and associated fluid pressures are shown in a 13 m / s wind, as well as an enlarged detailed cross-sectional view of the blade near the tip end.

[0096] Fig.12D Is a front view of the upstream surface of a blade of a flow deflector / blade assembly including a flow deflector (but with the flow deflector not shown in the figure), showing the pressure regions and associated fluid pressures in a 13 m / s wind.

[0097] Fig.12E Is a rear view of the downstream surface of a blade showing the benefits of no flow deflector, where the pressure regions and associated fluid pressures are shown in a 13 m / s wind.

[0098] Fig.12F Is a rear view of the downstream surface of a blade of a flow deflector / blade assembly including a flow deflector (but with the flow deflector not shown in the figure), where the pressure regions and associated fluid pressures are shown in a 13 m / s wind.

[0099] Figure 12G is Fig. 12C and Fig.12E An enlarged side isometric view of section “12G” of the blade, showing the surface pressures on the pressure (upstream) and suction (downstream) surfaces of that section.

[0100] Fig.12H is Fig.12D and Fig.12F An enlarged side isometric view of section “12H” of the blade (the flow deflector is not shown in the figure), showing the surface pressures on the pressure surface and suction surface of that section.

[0101] Fig.13A Is a cross-sectional view of the flow deflector / blade assembly, showing the angle of attack of two flow deflector profiles relative to the blade profile, where one flow deflector profile is closer to the oncoming fluid flow than the blade profile on the pressure side of the blade, and one flow deflector profile is farther from the oncoming fluid flow than the blade profile on the suction side of the blade.

[0102] Fig. 13B Is a cross-sectional view of the flow deflector / blade assembly, showing (i) the angle of attack of two flow deflector profiles relative to the blade profile, where one flow deflector profile is closer to the oncoming fluid flow than the blade profile on the pressure side of the blade, and one flow deflector profile is farther from the oncoming fluid flow than the blade profile on the suction side of the blade, and (ii) the relative difference seen when keeping the flow deflector angle of attack but moving the two flow deflector profiles closer to the oncoming fluid flow than shown in Fig.13A that figure.

[0103] Fig. 13C Is a front view of the disassembled flow deflector / blade assembly, not including any structure (one or more) connecting the flow deflector to the blade, and highlighting the deflection relative to the trailing edge of the blade in the chordal gap between the leading edges of the flow deflector at the tip end and hub end. For increased clarity of the chordal gap, the figure is not drawn to scale.

[0104] Fig.13D Is a rear isometric view of the flow deflector / blade assembly, not including any structure connecting the flow deflector to the blade, and highlighting the horizontal deflection relative to the trailing edge of the blade in the gap between the leading edges of the flow deflector at the tip end and hub end. For increased clarity of the horizontal deflection, the figure is not drawn to scale.

[0105] Fig.13E Is a cross-sectional view of the flow deflector / blade assembly, showing the flow deflector located on the suction side of the blade.

[0106] Fig.14AFront view of a partial-span fairing and blade assembly with an embodiment of a fixed connector assembly for retrofitting the partial-span fairing to a blade.

[0107] Fig. 14B Front cropped and enlarged view of a partial-span fairing and blade assembly with an embodiment of a fixed connector assembly for retrofitting the partial-span fairing to a blade.

[0108] Fig. 14C Cropped side cross-sectional view of a partial-span fairing and blade assembly with an embodiment of a fixed connector assembly for retrofitting the partial-span fairing to a blade.

[0109] Fig.14D Cropped side exploded isometric view of an embodiment of a partial-span fairing to blade connector assembly, with the blade and fairing not shown.

[0110] Fig.14E Cropped side isometric view of an embodiment of a partial-span fairing to blade connector assembly, with the blade and fairing not shown.

[0111] Fig.15 Front isometric view of a non-uniform thickness fairing, excluding any structure for attaching the fairing to the blade, showing (i) an enlarged detailed cross-sectional side view of the tip and center sections, and (ii) an enlarged detailed side view of the hub end.

[0112] Fig.16A Front view of an embodiment of a fairing / blade assembly with a curved fairing tip.

[0113] Fig. 16B Front cropped and enlarged view of an embodiment of a fairing / blade assembly with a curved fairing tip.

[0114] Fig.17A Front view of an embodiment of a fairing including an arcuate trailing edge near the tip, superimposed on a fairing without an arcuate trailing edge near the tip end.

[0115] Fig. 17B Enlarged detailed tip end view of an arcuate trailing edge superimposed on a fairing without an arcuate trailing edge.

[0116] Fig. 17C is superimposed on a fairing without an arcuate trailing edge Fig.17A Enlarged detailed cross-sectional view of the arcuate trailing edge at line C-C in

[0117] Fig.18A Front view of an embodiment of a fairing, showing a wall protruding from the upstream surface of the fairing.

[0118] Fig.18B Is a scaled-up isometric view of the cut-away splitter plate, showing the wall protruding from the upstream surface.

[0119] Fig.19A Is a rear view of an embodiment of a multi-part splitter plate / vane assembly with a fixed-link connector assembly, showing a cut-away, scaled-up detail rear view of the connection between two splitter plate sections, and a scaled-up, cut-away detail side cross-sectional view of the connection between two splitter plate sections.

[0120] Fig.19B Is a side isometric view of a two-part splitter plate to vane connector assembly, showing (i) a cut-away, scaled-up detailed isometric view of the connection between connector sections, and (ii) a cut-away, scaled-up detailed isometric exploded view of the connection between two connector sections.

[0121] Fig. 20A Is a rear isometric view of an embodiment of a splitter plate / vane assembly with a variable-angle connector assembly.

[0122] Fig. 20B Is a side view of the splitter plate chord in five positions relative to the rotor's plane of rotation, depicting four ranges of angle of attack of the splitter plate from the leading edge of the splitter plate closest to the oncoming fluid flow to the leading edge of the splitter plate furthest from the oncoming fluid flow. For increased clarity of the articulation, the figure is not drawn to scale and the splitter plate profile is not shown.

[0123] Fig. 20C Is a cut-away rear isometric view of a splitter plate / vane assembly with a variable-angle connector assembly, where the splitter plate is in the fully retracted position (its trailing edge is furthest from the oncoming fluid flow), and where the cut-away portion reveals the motorized components and the connection of the splitter plate to the connector assembly.

[0124] Fig.20D Is a cut-away rear isometric view of a splitter plate / vane assembly with a variable-angle connector assembly, where the splitter plate is in the fully extended position (its trailing edge is furthest from the oncoming fluid flow), and where the cut-away portion reveals the motor components and the connection of the splitter plate to the connector assembly.

[0125] Fig.20E Is an exploded rear view of the motor and associated main drivetrain components of a variable-angle connector assembly located within the vane. The vane is not shown to reduce the complexity of the illustration.

[0126] Fig.20F Is an exploded isometric view of the splitter plate end of a cut-away flexible rod assembly, where the cut-away portion reveals (i) a cross-sectional view of the splitter plate and (ii) internal details of the guide tube.

[0127] Figure 20GIs an exploded isometric view of a flexible rod assembly for use with a variable angle connector assembly, showing a cross-sectional view of a cut-away portion of a guide tube and internal details.

[0128] Fig. 20H Is a cropped and enlarged isometric view of a portion of a variable angle connector assembly for a deflector blade, where the cut-away portion shows a cross-sectional view of structural components and a guide tube component.

[0129] Fig.20I Is an enlarged isometric view of a guide tube assembly with a mating male key component.

[0130] Fig.21A Is a side profile schematic showing 10 points along the chord of a deflector blade, showing exemplary X and Y dimensions for an embodiment of the deflector blade.

[0131] Fig. 21B Is corresponding to Fig.21A A dimensional table.

[0132] Fig. 21C Is a side view of a deflector blade, showing a cutting line corresponding to Fig. 21B The cutting line.

[0133] Fig.21D Is a table of deflector blade spanwise dimensions measured from the tip of the deflector blade, corresponding to the tables in Fig. 21B And Fig. 21C In the tables.

[0134] Fig.22A Is corresponding to Fig. 22B An isometric view of a deflector blade and blade geometric coordinate system corresponding to the dimensional data table in

[0135] Fig. 22B Is a dimensional data table containing data describing the exemplary positioning and angles of a deflector blade relative to a blade, and corresponding to the simulated deflector blade / blade assembly described herein.

[0136] Detailed description

[0137] Unless otherwise defined, all technical terms, symbols, and other technical or specialized terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this disclosure pertains. If the definitions set forth in this section are contrary to or otherwise inconsistent with the definitions set forth in patents, applications, published applications, and other publications incorporated herein by reference, then the definitions set forth in this section shall prevail over the definitions incorporated herein by reference.

[0138] References in the specification to "one embodiment", "an embodiment", "another embodiment", "exemplary embodiment", "some aspects", "another aspect", "aspect", etc. indicate that the described embodiments may include a particular feature, structure, or characteristic, but every embodiment covered by the present disclosure may not necessarily include that particular feature, structure, or characteristic. Moreover, such phrases do not necessarily refer to the same embodiment. In addition, when a particular feature, structure, or characteristic is described in connection with an embodiment, such feature, structure, or characteristic is also described in connection with other embodiments whether or not explicitly described.

[0139] Unless otherwise stated or the context otherwise implies, as used herein, "a" or "an" means "at least one" or "one or more".

[0140] When describing the position and / or orientation or movement, force, or other dynamic action direction of a component, device, location, feature, or a part thereof, this description may use various terms describing relative spatial arrangement and / or orientation or direction. Unless specifically stated or otherwise specified by the context of the specification, these terms (including but not limited to top, bottom, upper, lower, beneath, above, over, below, left, right, front, rear, under, beside, adjacent, between, horizontal, vertical, diagonal, longitudinal, lateral, radial, axial, clockwise, counterclockwise, etc.) are used to conveniently refer to such components, devices, locations, features, or a part thereof or movement, force, or other dynamic actions represented in the drawings, and are not intended to be restrictive.

[0141] Unless otherwise stated or the context otherwise implies, the terms used herein to describe the physical and / or spatial relationship between a first component, structure, or a part thereof and a second component, structure, or a part thereof, e.g., attach, connect, fix, engage, link, couple, or similar terms or variations of such terms, shall include both a direct relationship in which the first component, structure, or a part thereof is in direct contact with the second component, structure, or a part thereof, or there is one or more intermediate components, structures, or a part thereof between the first component, structure, or a part thereof and the second component, structure, or a part thereof.

[0142] In addition, unless otherwise stated, any specific dimensions mentioned in this specification only represent an exemplary embodiment of the device embodying aspects of the present disclosure and are not intended to be limiting.

[0143] As used herein, within the scope of this document, the terms "first" and "second" before the name of an element (e.g., a component, a device, a location, a feature, or a part thereof, or the direction of a movement, a force, or other dynamic action) are used for identification purposes to distinguish similar elements and are not necessarily intended to imply an order. The terms "first" and "second" are also not intended to exclude the inclusion of additional similar elements. Additionally, the use of the term "first" before the name of an element (e.g., a component, a device, a location, a feature, or a part thereof, or the direction of a movement, a force, or other dynamic action) does not necessarily mean or require the existence of additional such elements (e.g., "second", "third", etc.).

[0144] As used herein, the term "fixed link", when used to refer to the physical arrangement between two or more items, means that one item is attached or connected to another item in a manner that precludes relative movement between the first item and the second item.

[0145] As used herein, when used to refer to the physical arrangement between two or more items, the term "operatively coupled" means that one item is attached or otherwise coupled to another item via a structure and / or mechanism that enables and / or effects relative movement between the first item and the second item such that the position and / or orientation of the first item relative to the second item can be selectively (including automatically) changed.

[0146] As used herein, the terms "optional" and "optionally" or the term "may" (e.g., as in the phrases "may include", "may comprise", "may produce", "may provide", or similar phrases) mean that the subsequently described component, structure, element, event, environment, characteristic, property, etc. may or may not be included or occur, and the description includes the cases where the component, structure, element, event, environment, characteristic, property, etc. are included or occur and the cases where they are not included or do not occur.

[0147] As used herein, the terms "substantially" and "substantial" refer to a considerable degree or extent. When used in conjunction with, for example, an event, an environment, a characteristic, or an attribute, these terms can refer to instances where the event, environment, characteristic, or attribute occurs exactly as described and instances where the event, environment, characteristic, or attribute occurs very nearly as described, e.g., taking into account the typical tolerance levels or variability of the embodiments described herein.

[0148] As used herein, the term "airfoil section" means a portion of a blade that has a shape that produces a pressure difference (lift) between opposing surfaces due to the relative movement of air with respect to the airfoil section.

[0149] As used herein, "apparent velocity" or "apparent flow rate" (alternatively, "effective velocity" or "effective flow rate") is the fluid flow to which the rotor blades are exposed, such as an air flow, a water flow, a liquid flow, or a gas flow, and is the vector sum of the oncoming fluid flow and the rotational flow caused by the rotation of the blades about the rotor axis of rotation.

[0150] As used herein, the term "bearing" refers to a component for supporting and / or guiding a rotating, oscillating, hinged, or sliding shaft, pivot, wheel, or assembly. Irrespective of the bearings described or shown, it can take various forms, including but not limited to sealed, unsealed, roller, ball, angular, needle, and thrust. However, unless otherwise specifically stated, when such a term is used, the term indicates that the actual link or coupling takes various forms, which will be apparent to one of ordinary skill in the art.

[0151] As used herein, the terms "blade", "rotor blade", and "turbine blade" refer to any embodiment of a blade used on a hydrodynamic turbine, including but not limited to wind turbines and hydro turbines.

[0152] As used herein, the term "blade angle of attack" refers to the angle of the blade chord or blade chord line at a given point along the blade span relative to the rotor plane of rotation.

[0153] As used herein, the term "bushing" refers to a component used as a guide for a component that rotates, slides, hinges, or otherwise moves within it, and can take various forms, including but not limited to self-lubricating, metal-polymer composite, bronze-wrapped, filament-wound, and injection-molded. However, unless otherwise specifically stated, when such a term is used, the term indicates that the actual connection or coupling takes various forms, which will be apparent to one of ordinary skill in the art in certain cases.

[0154] As used herein, the term "CAD model" refers to a virtual model of a part or combination of parts (including but not limited to a rotor, blade, deflector, or blade / deflector assembly) created using computer-aided design (CAD).

[0155] As used herein, the term "chord line" refers to a line passing through the leading edge and the trailing edge of a deflector or blade, which is collinear with the chord and can extend beyond the chord. When describing the blade or deflector angle of attack, this term can be used as a reference position relative to the rotor plane of rotation at a given point along the blade or deflector span.

[0156] As used herein, the term "chord" refers to the distance between the trailing edge and the point where the chord intersects the leading edge, sometimes shown as a line and / or used as a reference position relative to the rotor plane of rotation at a given point along the blade or deflector span. This term can be used when describing such a distance or the angle of attack in a deflector or blade.

[0157] As used herein, the terms "computer", "computer-controlled", and like terms refer to computing and control modules (e.g., system controllers) such as microprocessors, programmable logic controllers, embedded controllers, application specific integrated circuits (ASICs), and computers that are configured to implement computing and / or control steps by receiving one or more input values and executing one or more algorithms stored on a non-transitory machine-readable medium (e.g., software), the non-transitory machine-readable medium (e.g., software) providing instructions for manipulating or otherwise acting on or in response to the input values and outputting one or more output values. Such output may be displayed or otherwise indicated to a user to provide information to the user, such as information about the status of an instrument or a process being performed thereby, or such output may include an input to other processes and / or control algorithms and / or computers. Data input components include elements through which data is input for use by control and computing hardware components. Such data input may include signals generated by a computer, sensors, or scanners such as position sensors, velocity sensors, accelerometers, environmental (e.g., temperature and barometric pressure) sensors, motor encoders, barcode scanners, or RFID scanners, pressure sensors, as well as manual input elements such as keyboards, stylus-based input devices, touchscreens, microphones, switches, manually operated scanners, etc. Data input may also include data retrieved from memory. Data output components may include hard disk drives or other storage media, data transmission components (e.g., LAN, WiFi), monitors, printers, indicator lights, or audible signal elements (e.g., chimes, buzzers, horns, bells, etc.). A computer may include one or more uninterruptible power supplies.

[0158] As used herein, the term "connector assembly" refers to a structure that connects a splitter vane to a turbine blade.

[0159] As used herein, the term "recess" refers to a concave portion of a surface when shown as part of a profile.

[0160] As used herein, the term "protrusion" refers to a convex portion of a surface when shown as part of a profile.

[0161] As used herein, the term "splitter vane" means a structure configured to define a pressure surface and a suction surface when exposed to a relative fluid flow and positioned and oriented relative to an associated rotor or turbine blade to affect the fluid flow impinging on the associated blade, regardless of the orientation of the longitudinal axis (axis of rotation) of the rotor or the direction of rotor rotation.

[0162] As used herein, the term "deflector angle of attack" refers to the angle of the deflector chord or deflector chord line at a given point along the span of the deflector relative to the plane of rotation of the rotor.

[0163] As used herein, the term "deflector / vane assembly" or "turbine vane assembly" refers to any combination of a rotor or turbine vane and one or more deflectors, including all embodiments as described herein.

[0164] As used herein, the term "edge" refers to any intersection of the pressure side and the suction side of the deflector, where they meet and include, but are not limited to, arcs, decreasing and increasing radii, and decreasing and increasing curvatures.

[0165] As used herein, the term "flexible shaft" refers to a component configured to transmit force or rotational motion through a non-straight path, which is capable of withstanding axial compression or longitudinal tensile loads and is laterally flexible and compliant in its cross-section. Unless otherwise specifically stated, when such a term is used, the term indicates that the device can take various forms. The structure can include a core composed of wires, strands, or fibers wound in layers in opposite directions around a centerline or linear structure, and a housing composed of one or more similar or different material layers including metals, composites, cloth, plastics, and rubbers. The layers can include reinforcing weaves. Some flexible shafts can have all of these components, while other flexible shafts can have one or more of these components. In certain cases, the appropriate construction will be apparent to those of ordinary skill in the art.

[0166] As used herein, the term "flow simulation" refers to a computational fluid dynamics (CFD) simulation, also referred to herein as "flow analysis".

[0167] As used herein, the term "flow straightener" with respect to fluid flow refers to a device that reduces vortices and asymmetries in fluid flow.

[0168] As used herein, the term "global torque" refers to the combination of positive and / or negative torques on the turbine by all deflector and vane surfaces within the deflector / vane assembly, where the deflector / vane assembly is part of the turbine, and the global torque is always positive in the desired direction of rotation about the hub axis.

[0169] As used herein, the term "hub end" refers to the portion of the blade and / or deflector that is closest to the hub of the associated rotor as defined herein.

[0170] As used herein, the term "hydrofoil section" refers to a portion of the blade that has a shape that creates a pressure difference (lift) between opposing surfaces due to the relative motion of water or other liquid relative to the hydrofoil section.

[0171] As used herein, the term "hydraulic turbine" refers to a system designed to convert the kinetic fluid energy from a moving liquid or liquid mixture (including but not limited to water) into mechanical energy, also known as a "water turbine".

[0172] As used herein, the term "motor" refers to a machine that converts electrical power or pressure (including but not limited to hydraulic and pneumatic) into mechanical energy (such as rotational energy).

[0173] As used herein, the term "negative torque" refers to the torque component acting on the deflector and / or blade surface in a direction opposite to the desired rotation about the rotor axis of rotation.

[0174] As used herein, the term "positive torque" refers to the torque component acting on the deflector and / or blade surface in the desired direction of rotation about the rotor axis of rotation.

[0175] As used herein, when referring to a blade or deflector, the term "profile" refers to the chordwise section (i.e., from the leading edge to the trailing edge) of the blade or deflector, which shows the shape of the blade or deflector between the opposing upstream (pressure) and downstream (suction) surfaces.

[0176] As used herein, the term "pressure side" refers to the surface of a deflector or blade that is closer to the oncoming fluid flow or the region adjacent to that surface, also known as the "upstream", "windward", or "leeward" side.

[0177] As used herein, the term "pressure" in terms of fluid pressure is relative to atmospheric pressure. It is expressed as a positive number when greater than atmospheric pressure and as a negative number when less than atmospheric pressure. Positive pressure values are typically referred to as pressure or positive pressure, and negative pressure values are typically referred to as suction.

[0178] As used herein, the term "pressure surface" refers to the surface of a deflector or blade that is closer to the oncoming fluid flow, also known as the "upstream", "windward", or "leeward" side.

[0179] As used herein, the term "reflected arc" or "reflected mean camber line" refers to a mean camber line that has a reversal of curvature from its first direction, which causes it to bend chordwise at the trailing edge of the deflector. The center of curvature of the reflected mean camber line is located on the downstream side or suction side of the deflector or blade for one portion of the mean camber line and on the upstream (or pressure) side of the deflector or blade for another portion of the mean camber line.

[0180] As used herein, the term "right-angle drive" means a mechanism having a gear train that can transmit input torque and rotational motion laterally (e.g., 90 degrees). A right-angle drive can be configured with (i) an input shaft that, when powered, rotates an output shaft at a 90° angle, and (ii) an optional additional output shaft that is collinear with the input shaft and is rotated and driven by the input shaft (commonly referred to as a three-way right-angle drive or three-way right-angle gearbox).

[0181] As used herein, the term "rotational flow" means a fluid flow caused by the rotation of a blade about the rotor axis of rotation and which is a component of the apparent velocity.

[0182] As used herein, the term "rotor" means a combination of wind or water turbine blades.

[0183] As used herein, the term "rotor blade" is synonymous with the term "turbine blade" and means a wind or water turbine blade that is part of a rotor.

[0184] As used herein, the term "seal" refers to a device or substance that serves as a fluid barrier to prevent fluid exchange in a static, low / high pressure, or vacuum environment. Regardless of how it is shown, its application can take many forms, including but not limited to physical seals between media / environments, coatings that prevent the exchange of media or fluids through porous surfaces, gaskets, O-rings, packings, shaft seals, coatings, and adhesives. However, unless specifically stated otherwise, when using such terms, these terms indicate that the actual seal can take many forms, which will be apparent to one of ordinary skill in the art in certain cases.

[0185] As used herein, the term "swept volume" means the three-dimensional space through which a deflector or blade travels about the rotor axis of rotation.

[0186] As used herein, the term "suction" with respect to fluid pressure is relative to atmospheric pressure and is expressed as a negative number. It is also commonly referred to as negative pressure.

[0187] As used herein, the term "suction side" refers to the surface or area near the surface of a deflector or blade that is opposite or generally opposite to the pressure-side surface and further away from the oncoming flow, also referred to as the "downwind" or "downstream" side.

[0188] As used herein, the term "suction surface" refers to the surface of a deflector or blade that is opposite or generally opposite to the pressure-side surface and further away from the oncoming flow, also referred to as the "downstream" or "downwind" side.

[0189] As used herein, the term "tip end" refers to the portion of a blade and / or deflector that is closest to its respective tip end.

[0190] As used herein, the term "VAC component" refers to a variable angle connector component that connects a deflector to a turbine blade and enables the orientation of the deflector relative to the turbine blade to be changed.

[0191] As used herein, the term "wind turbine" refers to a system designed to convert the kinetic fluid energy from a moving gas or gas mixture (including but not limited to air) into mechanical energy.

[0192] As used herein, the term "working section" refers to a portion of a blade that has a shape that creates a pressure difference (lift) between opposing surfaces due to the relative movement of a fluid (such as air, water, or other liquid or gas). The working section may be referred to as an airfoil section on a wind turbine blade and, on a hydro turbine blade, may be referred to as a hydrofoil section.

[0193] All possible combinations of elements and components described in the specification or recited in the claims are contemplated and considered to be part of the present disclosure. It should be understood that all combinations of the concepts discussed in more detail below (provided these concepts are not mutually inconsistent) are considered to be part of the subject matter disclosed herein.

[0194] Preferred embodiments will now be described with reference to the drawings, in which like numerals, including those followed by letters or hyphens and letters such as "-A", refer to like elements throughout. The terms used in the following description, including but not limited to the words "upper" and "lower", should not be construed in any limited or restrictive way merely because they are used in conjunction with a detailed description of certain specific embodiments. Additionally, for ease of understanding the drawings, many of the components described herein and shown in the drawings are drawn as solid components. Although such components are cross-hatched, all such components can be manufactured using (i) conventional assembly techniques and (ii) conventional weight-saving methods, whereby a single component can be divided into multiple parts and, when reassembled, embody the characteristics of the components described herein and / or shown in the drawings. Conventional weight-saving methods include but are not limited to designing all such components as multiple sub-assemblies that can be assembled into the specific component as shown using conventional assembly techniques. Depending on the designer's choice, all components may also have an internal lattice or other non-solid internal design and an external skin, with reinforced and / or thickened areas as needed, such as in areas that contact bearings or supports, whereby these components may appear solid while in fact they do not need to be solid to achieve their desired function.

[0195] Provided herein and shown in the drawings is a configuration of a deflector that can be fixedly linked and / or operably coupled to one or more wind or hydro turbine blades.

[0196] The embodiments disclosed herein permit a variety of configurations of the dimensions and shapes of the flow deflectors, including but not limited to (i) different aspect ratios (the ratio of chordwise width to spanwise length) of the flow deflectors, and (ii) the position relative to the pressure side and the suction side of the respective blade to which the flow deflectors are fixedly linked or operatively coupled. Additionally, the description and the drawings are not intended to limit the physical shape, dimensions, mounting location of the flow deflectors, or the type of fluid in which the flow deflectors operate.

[0197] 1. Prior Art - Wind Turbine Figure 1A-Figure 2D

[0198] Now referring to Figure 1A , the fluid flow turbine 100 is an example of an embodiment disclosed herein. The fluid flow turbine 100 may include a horizontal axis wind turbine (“HAWT”). The fluid flow turbine 100 includes a rotor 110, which includes a plurality of rotor blades 111 (e.g., three), the rotor blades 111 being mounted to a hub 121 and extending radially from the hub 121, the hub 121 defining a rotor axis or rotor rotation axis 123 (also referred to herein as the hub axis or hub rotation axis), and the rotor 110 rotating about this axis in direction 5 (counterclockwise in the illustrated embodiment). In alternative embodiments, the rotor 110 includes more or fewer than three rotor blades 111 and / or rotates clockwise.

[0199] Now referring to Figure 1B and still referring to Figure 1A , a typical fluid flow turbine 100 may include rotor drive components, such as a gearbox 126 and a generator 128 located within a nacelle 138, which are operatively coupled to the rotor 110 or define the axis of rotation 123 of the rotor 110, and the rotor 110 converts the kinetic energy of the oncoming fluid flow (wind flow) 1 into rotational energy utilized within the gearbox 126 via the rotor blades 111. The gearbox 126 is rotated by the rotor 110 and may be coupled to a device for converting the rotational energy, such as a generator 128 or a fluid pump (not shown). It should be noted that some wind turbines may use a direct drive generator directly coupled to the rotor 110 and eliminate the need for the gearbox 126.

[0200] The turbine 100 (i.e., the rotor 110 and the nacelle 138) may be mounted on top of a tower 124 that defines a tower axis 125. Wind speed and wind direction sensors 139 may be mounted on the nacelle 138 and connected to a computer (not shown) for monitoring wind turbine operation, e.g., orienting the rotor 110 perpendicular to the oncoming fluid flow 1 and pitching the rotor blades 111.

[0201] Now referring to Figure 2A and Figure 2B , each rotor blade 111 includes, relative to the hub 121 (see Figure 1A ) at the inner end of the blade root 158, and may include a connection structure 157 (e.g., an annular mounting flange) for fixing the rotor blade 111 relative to the hub 121, and a blade tip 151 at the radially outer end of the rotor blade 111 relative to the hub 121, and defining a span 154 from the blade root 158 to the blade tip 151. The rotor blade 111 may include a root section 160 advancing from the blade root end 158 and an airfoil section 164 having a leading edge 168 and a trailing edge 174. The cross-sectional profile of the root section 160 at the far root end 158 of the blade may be generally circular, elliptical, oval, or egg-shaped. The airfoil section 164 is the working section of the rotor blade 111 and defines an airfoil profile between the leading edge 168 and the blade trailing edge 174, which forms a generally facing oncoming fluid flow 1 (see Figure 1A ) the pressure surface (or upstream surface) 178 and the suction surface (or downstream surface) 182 (see Figure 2B ).

[0202] Each rotor blade 111 also includes a tip section 150 overlapping a portion of the airfoil section 164 and a leading edge 168 and a blade trailing edge 174 defining the boundaries of the pressure surface 178 and the suction surface 182. Referring to Figure 2A Details A, B, and C of, the pressure surface 178 may include a front convex portion 181 and a rear concave portion 180. The blade 111 may include a transition section 184 at which the cross-sectional shape of the rotor blade 111 transitions from the circular, elliptical, or other shape of the blade root 158 and the root section 160 to the shape of the airfoil section 164. In an alternative environment, the transition section is omitted, and the blade 111 includes a sudden, generally instantaneous transition between the profile of the root section 160 and the profile of the airfoil section 164.

[0203] The airfoil section 164 is defined by a chord 186 between the blade leading edge 168 and the blade trailing edge 174. The chord 186 may be variable along the span 154 of the blade 111 (e.g., the chord decreases as the span distance from the blade root 158 increases, as shown in the figure), or the chord 186 may be constant along part or all of the span 154 within the airfoil section 164.

[0204] Now referring to Figure 2C , and still referring to Figure 2A , the airfoil section 164 may have an aerodynamic profile defined by the pressure surface 178 and the suction surface 182, which defines a mean camber line 188 having a maximum camber 190 and a maximum thickness 192. The maximum thickness 192, the maximum camber 190, and the mean camber line 188 may vary with the spanwise distance from the hub 121 (see Figure 1A and Figure 2A Details A, B, C). The chord 186 may be arranged at the blade chord angle (or angle of attack) 194 with respect to the rotational plane 104 of the rotor 110 (see Figure 1A ), and the blade chord angle 194 may also vary with the spanwise distance from the hub 121.

[0205] Now referring to Figure 2C , the blade 111 may have an internal support structure including (i) a spar 114 and stiffeners 112 on the pressure side 178, (ii) a spar 115 and stiffeners 113 on the suction side 182, and (iii) stiffeners 118 at and near the leading edge 168 (collectively referred to as "blade stiffeners").

[0206] The blade 111 may also have a U-shaped shear web 116 near the center of the blade 111 and a U-shaped shear web 117 near the leading edge 168 of the blade (collectively referred to as "shear webs"). The stiffeners and shear webs provide additional structural support for the blade 111.

[0207] 1.1 Apparent velocity

[0208] Referring to Figure 2D , when the rotor 110 is stationary, i.e., not rotating, each rotor blade 111 is only exposed to the oncoming fluid flow 1 impinging on the pressure surface 178 of the blade 111. As the flow passes over the trailing edge 174 and the leading edge 168 of the blade, this passage of the flow causes a pressure drop on the suction side 182. The passing flow moving in the downwind direction creates recirculation and a vacuum in the region adjacent to the suction side 182 (i.e., the pressure is relatively lower than the pressure on the pressure side 178). If the suction on the suction surface 182 is lower between the leading edge 168 and the thickest part of the blade than the suction between the thickest part of the blade 111 and the trailing edge 174 of the blade, a positive rotor torque is generated.

[0209] When the rotor 110 rotates, each rotor blade 111 is exposed to the flow caused by the movement of the rotor blade 111 in the rotational direction 5 within the rotor plane 104 (see Figure 1A ) and the oncoming fluid flow 1. The result of the flow caused by the rotational direction 5 and the oncoming fluid flow 1 is the apparent velocity ("AV") or apparent fluid flow. A portion of the apparent velocity AV flows over the pressure side 178 of the blade 111, and a portion of the apparent velocity AV flows over the suction side 182 of the blade 111. Due to the different curvatures of the pressure side 178 and the suction side 182 and / or the angle of attack of the blade 111 (i.e., the angle between the apparent velocity AV and the rotor plane 104), the fluid flows faster on the suction side 182 than on the pressure side 178, thereby creating a pressure difference between the suction side 182 and the pressure side 178, resulting in a lift force F that generally acts perpendicular to the direction of the apparent velocity AV LIn addition, the flow on the blade 111 generates a drag force F acting in a direction parallel to the apparent velocity AV. D The lift force F L component generates a positive torque F acting on the blade 111 T+ , and the drag force F D component results in a negative torque F acting on the blade 111 T- . A F greater than F T- causes the rotor to rotate. T+

[0210] 1.2 Beneficial regions Figure 2E-2F

[0211] Now referring to Figure 2E and Figure 2F , the blade 111 has regions on its pressure surface 178 and suction surface 182, whereby, depending on the curvature of the respective surface, both the pressure and the suction can result in a positive or negative torque acting on the blade 111. This subsection describes the geometry of the blade 111 and its relevant angles of attack that cause positive pressure or negative pressure (suction) to generate positive torque. These regions are defined herein as "beneficial regions".

[0212] Under theoretically ideal conditions ("ideal conditions"), and depending on the blade geometry and angle of attack as described below, the beneficial regions can have positive pressure or negative pressure that contributes positive torque to the blade 111.

[0213] The pressure surface 178 includes region 10, which under ideal conditions will have (i) a positive pressure located between the transition point 9 (in the illustration, which corresponds to the trailing edge 174 of the blade) and the transition point 11, and (ii) a negative pressure (suction) in region 12 located between the transition point 11 and the transition point 13 (in the illustration, which corresponds to the leading edge 168).

[0214] The suction surface 182 includes a region that under ideal conditions will have (i) a negative pressure (suction) in region 14 located between the transition point 13 and the transition point 15, and (ii) a positive pressure in region 16 located between the transition point 15 and the transition point 17 (in the illustration, which corresponds to the trailing edge 174 of the blade).

[0215] 1.3 Beneficial regions - How they work Figure 2G

[0216] Now referring to Figure 2G , while still referring to Figure 2E and Figure 2F ​, any pressure or suction on the blade 111 can be described as a series of forces acting normal (locally perpendicular) to the blade pressure surface 178 or suction surface 182. Any force applied to the blade 111 can be decomposed into an axial component (i.e., in a direction parallel to the rotor rotation axis 123 (see Figure 1A )) and a tangential component (i.e., in a direction perpendicular to the rotor rotation axis 123). The axial force does not directly affect the rotation of the blade 111. The tangential component of the force in the expected rotation direction 5 increases the positive torque and is thus beneficial. The tangential component of the force opposite to the rotation direction 5 results in a negative torque and is thus harmful.

[0217] The greater the slope of the blade pressure surface 178 relative to the rotor rotation plane 104 (e.g., 178 - A, 178 - B, and 178 - C) and the greater the slope of the blade suction surface 182 relative to the rotor rotation plane 104 (e.g., 182 - A, 182 - B, and 182 - C), the greater the tangential component of the force becomes, since the force is applied normal to the surface.

[0218] For example, since the angle of slope 178 - A is 30 degrees and greater than slope 178 - B (14 degrees), the same pressure at the two slopes will produce a greater force in the rotation direction at slope 178 - A than at slope 178 - B. If the tangential component is in the rotation direction 5, this force is beneficial. When the set of forces generated by the pressure all have a tangential force component in the rotation direction 5, region 10 produces a beneficial torque.

[0219] In the case where the normal force makes a greater slope angle with the rotor rotation axis 123 (see Figure 1A ), such as 178 - A, 178 - C, and 182 - C, the greatest beneficial force is experienced, since the tangential component of the force in the direction 5 is greater than elsewhere in the example shown. The theoretically ideal pressure and suction positions are as follows:

[0220]

[0221] 1.4 Effect of Angle of Attack on the Beneficial Region - Figure 2F and Figure 2F Detail A of

[0222] Now refer to Figure 2F, when the angle of attack of the blade 111 changes, the beneficial regions can move along the blade chord 186. For example, in the case of an angle of attack of -5 degrees as shown in the figure, the blade 111 has a beneficial region 12 where suction ideally occurs and a beneficial region 10 where pressure ideally occurs. However, when the blade trailing edge 174 pitches towards the oncoming flow 1 at an angle of attack of 12 degrees, for example, (i) the transition point 9 moves towards the oncoming flow 1 and down towards the leading edge 168, thereby reducing the area of the beneficial region 10, and (ii) a third beneficial pressure surface region 10-A is formed between the transition point 9 and the transition point 9-A (see Figure 2F Detail A). Ideally, the region 10-A will benefit most from suction and actually benefits from reduced pressure to contribute positive torque in the desired rotational direction 5 of the blade 111.

[0223] 2. Prior Art - Hydroturbine Figure 3

[0224] Now refer to Figure 3 , the fluid flow hydroturbine 300 is an example of an embodiment disclosed herein. The fluid flow turbine 300 may include a horizontal axis hydroturbine. The fluid flow turbine 300 includes a rotor 310 that includes a plurality (e.g., three) rotor blades 311 that are mounted to a hub 321 and extend radially from the hub 321, the hub 321 defining a rotor axis 323 about which the rotor 310 rotates in a direction 5 (counterclockwise in the illustrated embodiment). In alternative embodiments, the rotor 310 includes more or fewer than three rotor blades 311 and / or rotates clockwise.

[0225] The fluid flow turbine 300 may include a rotor drive component, such as a gearbox 326 and a generator 328 located within a nacelle 338, which are operably coupled to the rotor 310 or define the rotor axis 323 of the rotor 310, and the rotor 310 converts the kinetic energy of the oncoming fluid flow (water flow) 1 into rotational energy utilized within the gearbox 326 via the rotor blades 311. The gearbox 326 is rotated by the rotor 310 and may be coupled to a device that converts the rotational energy, such as a generator 328 or a fluid pump (not shown). It should be noted that some fluid flow turbines may use a direct drive generator directly coupled to the rotor 310 and eliminate the need for the gearbox 326.

[0226] The turbine 300 (i.e., the rotor 310 and the nacelle 338) may be mounted to a tower 324 that defines a tower axis 325. Fluid velocity and fluid direction sensors 339 may be mounted on the nacelle 338 and connected to a computer (not shown) for monitoring the operation of the hydroturbine, e.g., orienting the rotor 310 perpendicular to the oncoming fluid flow 1 and pitching the rotor blades 311.

[0227] Now refer to Figure 4A and Figure 4B , each rotor blade 311 includes a blade root 358 at its inner end relative to the hub 321 (see Figure 3 A), and may include a connection structure 357 (e.g., an annular mounting flange) for fixing the rotor blade 311 relative to the hub 321 (see Figure 3 A), and a blade tip 351 at the radially outer end of the rotor blade 311 relative to the hub 321, and defines a span 354 from the blade root 358 to the blade tip 351. The rotor blade 311 may include a root section 360 advancing from the blade root end 358 and a hydrofoil section 364 having a leading edge 368 and a trailing edge 374. The cross-sectional profile of the root section 360 at the distal root end 358 of the blade may be generally circular, elliptical, oval, or egg-shaped. The hydrofoil section 364 is the working section of the rotor blade 311 and defines a hydrofoil profile between the leading edge 368 and the trailing edge 374, and this hydrofoil profile forms a pressure surface (or upstream surface) 378 that generally faces the oncoming fluid flow 1 (see Figure 3 ) and a suction surface (or downstream surface) 382 (see Figure 4B ).

[0228] Each rotor blade 311 also includes a tip section 350 that overlaps the hydrofoil section 164, and the pressure surface 378 may include a front convex portion 381 and a rear concave portion 380. The blade 311 may include a transition section 384 at which the cross-sectional shape of the rotor blade 311 transitions from the circular, elliptical, or other shape of the blade root 358 and the root section 360 to the shape of the hydrofoil section 364. In an alternative environment, the transition section is omitted, and the blade 311 includes a sudden, generally instantaneous transition between the profile of the root section 360 and the profile of the hydrofoil section 364.

[0229] The hydrofoil section 364 is defined by a chord 386 between the blade leading edge 368 and the blade trailing edge 374. The chord 386 may be variable along the span 354 of the blade 311 (e.g., the chord decreases as the span distance from the blade root 358 increases, as shown), or the chord 386 may be constant for the portion within the hydrofoil section 364 along the span 354.

[0230] The hydrodynamic interaction with the blade 311 is similar to that described in Subsection 1.1 above.

[0231] 3. Deflector position, length, and orientation relative to the blade- Figure 5A-Figure 8

[0232] The deflector / vane assembly (or turbine vane assembly) as described herein includes rotor blades (of a wind turbine, a water turbine, or other fluid flow turbine), where the deflector is fixed or otherwise coupled to the associated rotor blade. The deflector as described herein can be configured to work with rotor blades that rotate clockwise or counterclockwise.

[0233] Now referring to Figure 5- Figure 8 , a deflector (including but not limited to the partial span deflector as described herein) can be configured in a wind turbine 100 (see Figures 5 and Figure 6 ), a water turbine 300 (see Figure 7 and Figure 8 ) or other hydrodynamic turbines. In all fluid types, the deflector similarly affects the fluid flow adjacent and / or near the deflector / vane assembly. Since the interaction between the deflector as described herein and the associated rotor blade and the relative impact on rotor performance are generally independent of the type of fluid (such as air, water, liquid or gas) in which the rotor operates, the following description will refer to wind turbines, and it should be understood that these descriptions generally apply equally to other fluid turbines, such as water turbines.

[0234] Compared with a blade 111 without one or more deflectors, the deflector 200 or the partial span deflector 200-A (see Figures 5 and Figure 6 respectively) is positioned adjacent to the pressure side 178 of the blade 111 coupled to the deflector and closer to the oncoming flow than the blade, or positioned adjacent to the suction side 182 and farther from the oncoming flow than the blade 111 (see Figure 2A and Figure 2B ), causing the fluid pressure on the pressure side 178 of the blade 111 to increase and / or the fluid pressure on the suction side 182 of the blade 111 to decrease, thereby generating a greater global torque in a rotor with blades having deflectors compared to a rotor with the same blades but without deflectors. In this context, the deflector being coupled to the associated blade means that the deflector is fixedly linked to the associated blade (attached or connected in a manner that prevents relative movement between the deflector and the associated blade) or operably coupled to the associated blade (attached or otherwise coupled to the associated blade via a structure and / or mechanism that enables and / or implements relative movement between the deflector and the associated blade), such that the position and / or orientation of the deflector relative to the associated blade can be selectively (including automatically) changed.

[0235] Now referring to Figure 5A and Figure 2A, each flow deflector 200 is configured to affect the entire airfoil section 164 of the associated blade 111 to which it is coupled (i.e., the flow deflector 200 extends spanwise along all or substantially all of the airfoil section 164), and each flow deflector 200 is positioned behind the leading edge 168 of the associated blade relative to the direction of rotation 5, on the pressure side 178 of the associated blade 111. One or more additional flow deflectors 200 may also be configured on the pressure side 178 or the suction side 182 of each blade 111.

[0236] 3.1 Flow Deflectors and Blade Swept Volumes

[0237] Now referring Figure 5B , in one embodiment, the flow deflector 200 operates in a separate and distinct swept volume in a region closer to the oncoming fluid flow 1 than the blade 111. For example, the flow deflector swept volume 35 is closer to the oncoming flow 1 than the blade swept volume 60.

[0238] The rotor 101 is shown as including three flow deflector / blade assemblies, each flow deflector / blade assembly including a flow deflector 200 and a blade 111. In this embodiment, a portion of each flow deflector 200 is positioned within an outer flow deflector swept volume 30 that is defined by (i) a circumferential travel path 31 of the flow deflector tip 218 about the hub rotation axis 123 at or near the flow deflector tip 218 and (ii) an inner circumference 33 located closer to the hub rotation axis 123.

[0239] The flow deflector swept volume depth (i.e., the axial extent relative to the hub rotation axis 123) 32 encompasses the flow deflector chord over its spanwise distance from its tip 218 to the circumference 33.

[0240] A smaller diameter transition swept volume 40 is shared by a portion of the flow deflector 200 and a portion of the blade 111, whereby as the distance of the flow deflector 200 from the hub rotation axis 123 decreases, the geometry of the flow deflector 200 begins to transition to be closer to the blade 111. The transition swept volume 40 is defined by the outer circumference 33 and the inner circumference 41.

[0241] The minimum diameter region (common swept volume 50) is entirely shared by a portion of the flow deflector 200 and a portion of the blade 111. The common swept volume 50 is defined by its outer circumference 41 and a circumferential travel path 51 of the flow deflector hub end 214 about the hub rotation axis 123 at or near the flow deflector hub end 214.

[0242] The spoiler 200 and the rotor blade 111 share the entire common swept volume 50, where the distance of the spoiler 200 from the oncoming fluid flow 1 increases as its spanwise distance towards the axis of rotation 123 decreases. That is, advancing from the tip end 218 to the hub end 214, the spoiler 200 advances a smaller distance towards the oncoming flow 1 compared to the blade 111.

[0243] The blade 111 has a separate swept volume 60, which is defined by the circumferential travel path around the hub axis of rotation 123 at its tip end 151 (slightly beyond the circumference 31 of the spoiler 200) and the inner circumference 33. The blade swept volume depth 65 includes the chord of the blade 111 in its spanwise distance from its tip 218 to the circumference 33.

[0244] The spoiler 200 as described herein has forty-eight percent (48%) of its span within its outer swept volume 30, twenty-five percent (25%) of its span within the transition swept volume 40, and twenty-seven percent (27%) of its span within the common swept volume 50. The virtual and physical properties of this embodiment are described in Section 7.

[0245] 3.2 Partial Span and Hydro Turbine Blades

[0246] Now referring to Figure 6 and still referring to Figure 2A each partial span spoiler 200 - A is configured to affect a portion of the airfoil section 164 of the associated blade 111 to which it is attached (i.e., the partial span spoiler 200 - A extends less in the spanwise direction than the entire airfoil section 164), and each partial span spoiler 200 - A is positioned behind the leading edge 168 of the associated blade with respect to the direction of rotation 5, on the pressure side 178 of the associated blade 111. One or more additional partial span spoilers 200 - A may also be configured on the pressure side 178 or the suction side 182 anywhere along the blade span 154.

[0247] Now referring to Figure 7 and Figure 4A each spoiler 400 is configured to affect the entire hydrofoil section 364 and the tip 351 of the associated blade 300 to which it is attached (see Figure 4A )(i.e., the spoiler 400 extends spanwise over all or substantially all of the hydrofoil section 364), and each spoiler 400 is positioned behind the leading edge 368 of the associated blade on the pressure side 378 with respect to the direction of rotation 5. One or more additional spoilers 400 may also be configured on the pressure side 378 or the suction side 382 of each blade 311.

[0248] Now referring to Figure 8, each partial-span splitter 400-A is configured to affect a portion of the hydrofoil section 364 of the associated blade 311 to which it is attached (see Figure 4A )(i.e., the partial-span splitter 400-A extends in the spanwise direction over less than the entire hydrofoil section 364), and the partial-span splitter 400-A is positioned behind the leading edge 368 of the associated blade with respect to the direction of rotation 5, on the pressure side 378 of the associated blade 311. One or more additional partial-span splitters 400-A may also be configured along any position of the blade span 354 on the pressure side 378 or the suction side 382 of each hydroturbine blade 311.

[0249] The partial-span splitters are designed for retrofitting existing turbines that are located at positions where the fluid flow in which they operate is less than that required to reach rated capacity.

[0250] Any splitter type, such as 200, 200-B, 201, may be configured as a partial-span splitter for a turbine operating with any fluid type.

[0251] As described in Sections 6 and 9.7 respectively, the splitters described herein may be fixedly linked or operably attached to the associated blades.

[0252] 4. General Shape of the Splitter and Orientation with Respect to the Oncoming Flow- Figure 9A-9B

[0253] Now refer to Fig.9A , which shows a front isometric view of the splitter 200, bounded by a leading edge 208, a hub end 214, a trailing edge 212, and a tip end 218. In the illustrated embodiment, the overall shape of the perimeter of the splitter 200 is trapezoidal, where the perimeter is bounded by the leading edge 208, the hub end 214, the trailing edge 212, and the tip end 218. However, in other embodiments, the shape of the perimeter may not be generally trapezoidal and may be, for example, quadrilateral.

[0254] The splitter 200 has a length defined by a splitter span 223 that extends from the splitter tip end 218 to the splitter hub end 214, and may be greater than, less than, or equal to the blade span 154 (see Figure 2A ). Each splitter 200 is positioned and oriented with respect to its associated blade 111 (see Figure 5) so as to have a pressure surface (or upstream surface) 204 that is impacted by the oncoming fluid flow 1 and a suction surface (or downstream surface) 206 that is opposite the pressure surface 204.

[0255] The splitter 200 at any position along the span 223 is characterized by a chord extending from the leading edge 208 to the trailing edge 212, such as the tip chord 224-A and the hub chord 224-E. The tip chord 224-A and the hub chord 224-E can be different, including but not limited to, such that (i) when unequal as shown, the perimeter of the pressure surface 204 of the splitter 200 is generally trapezoidal, and (ii) when equal, the perimeter of the pressure surface 204 of the splitter 200 is generally quadrilateral.

[0256] In one embodiment, the spanwise curvature of the leading edge 208 of the splitter 200 follows the curvature of the blade trailing edge 174 (see Fig. 9B ). In other embodiments, the leading edge 208 of the splitter 200 can be straight or have a curvature that does not follow the curvature of the blade 111 or other geometry.

[0257] The splitter 200 can be twisted along the span 223 similar to blade twist, and the twist can be (i) linear or non-linear, and / or (ii) can or can not match the twist of the blade to which it is fixedly linked or operably coupled. Flow analysis shows that matching the splitter twist to the blade twist will increase the performance of the blade / splitter assembly by increasing the global torque generated by the blade / splitter assembly in the rotational direction.

[0258] Now referring to Fig.9A Details A - C, still referring to Fig.9A , the pressure surface 204 has a rear concavity 230 that starts at the trailing edge 212 and ends at the transition point 236 and a front convexity 238 that starts at the transition point 236 and ends at the leading edge 208.

[0259] The splitter 200, the splitter 400 (see Figure 7 ) and all splitter embodiments described herein can be constructed of a single material or a combination of two or more materials (e.g., laminates), including but not limited to composite materials, plastics or metals, each having an integral support, including but not limited to a structural mounting flange, and / or a combination of materials and internal support structures common to turbine blade and / or airfoil construction methods, including but not limited to foam, ribs, spars or other stiffeners.

[0260] 5. Concavities and Convexities - Overview - Figure 9C-D

[0261] Now referring to Fig. 9C and Fig.9D , in the illustrated embodiment, the curvatures of the rear concavity 230 and the front convexity 238 can vary along the span 223 of the splitter 200 (see Fig.9A) vary uniformly or non-uniformly thereon, wherein the rear recess 230 and the front protrusion 238 at the tip end ( Fig. 9C ) have a greater curvature (smaller radius of curvature) than the rear recess 230 and the front protrusion 238 at the hub end ( Fig.9D ).

[0262] In other embodiments, the rear recess 230 and the front protrusion 238 may remain constant over at least part of the span of the vane and / or vary non-uniformly (increase or decrease in curvature) over the span 223 (see Fig.9A ).

[0263] 5.1 Relationship between the recess and protrusion and the angle of attack - Figure 9C-D

[0264] Each of the rear recess 230 and the front protrusion 238 can be characterized at any position along the span 223 of the deflector 200 (see Fig.9A ) by its respective depth, which is the maximum distance from the chord at that span position to the pressure surface 204 within the rear recess 230 or the front protrusion 238, and this depth is a function of the curvature (radius of curvature) and the arc length (or span) of the recess 230 or the protrusion 238.

[0265] Fig. 9C and Fig.9D the protrusions 238 shown in are exaggerated to more easily show their depth measurements.

[0266] Now referring to Fig. 9C , at the tip 218 of the deflector 200, the depth of the rear recess 230 is the length 234 when measured from the tip end chord 224 - A to the pressure surface 204, and the depth of the front protrusion 238 is the length 240 when measured from the tip end chord 224 - A to the suction surface 206.

[0267] Now referring to Fig.9D , at the hub end 214 of the deflector 200, the depth of the rear recess 230 is the length 248 when measured from the hub end chord 224 - E to the pressure surface 204, and the depth of the front protrusion 238 is the length 257 when measured from the hub end chord 224 - E to the suction surface 206. In the illustrated embodiment, the combination and arrangement of the rear recess 230 and the curvature reversal occurring at the front protrusion 238 result in across the span 223 of the deflector 200 (see Fig.9A) the reflection arc 226. The center of curvature of the reflection mid-arc 226 is located on the downstream or suction side (i.e., outside the downstream surface 206) of the deflector 200 for a portion of the mid-arc 226 corresponding to the convex portion 238, and on the upstream (or pressure) side (i.e., outside the upstream surface 204) of the deflector for another portion of the mid-arc 226 corresponding to the concave portion 230. The concave portion 230 or the convex portion 238 may not be circular, and either portion may have multiple centers of curvature on the downstream side or the upstream side of the deflector. Other embodiments may be configured without a lower convex portion and thus without a reflection arc.

[0268] Note that due to the concave portion 230 and the convex portion 238 (the degree of which may be exaggerated in the drawings to enhance the visualization of these concepts), at least a portion of the line representing the chord 224-A ( Fig. 9C ) and at least a portion of the line representing the chord 224-E ( Fig.9D ) may be located outside the deflector 200 (i.e., outside the space between the upstream surface 204 and the downstream surface 206). In some embodiments, most of the deflector chord 224 spanning the span 223 (see Fig.9A ) is outside the deflector 200. In some embodiments, the amount of the deflector chord outside the deflector profile that may vary along the span of the deflector is 25 - 80% of the chord at the tip end of the deflector and 65 - 90% of the chord at the hub end of the deflector, and may vary continuously, such as linearly, from the tip end to the hub end.

[0269] The concave depths 234, 248 and the convex depths 240, 257 (i) correspond to the curvature, whereby as the corresponding depth increases, the corresponding curvature increases (the radius of curvature decreases), and (ii) may vary between the tip end 218 and the hub end 214 of the deflector (see Fig.9A ).

[0270] In one embodiment, as described below, (i) there is a relationship between the depth of the camber 230 over the length of the span 223 (see Fig.9A ) and (ii) the angle of attack of the deflector 200.

[0271] Flow simulations show that in those having as Fig.9EIn the illustrated embodiments of the deflector / vane relative positions, (i) a recess depth 234 and 248 of five to twenty percent (5 - 20%) of the respective chords 224 - A to 224 - E, (ii) a protrusion depth 240 and 257 of zero to fifteen percent (0 - 15%) of the respective chords 224 - A to 224 - E, and (iii) an angle of attack of 0 - 15 degrees (the angle of attack is equal to 0 degrees when coplanar with the plane of rotation, and increases positively as the trailing edge of the deflector moves forward into the oncoming flow) increase the global torque depending on the relationship between the amount of convexity and concavity and the angle of attack of the deflector relative to the plane of rotation of the rotor, as further described below. However, due to the large number of optimization variables and alternative embodiments that can be combined, improvements in global torque can be obtained with an expanded range of deflector angles of attack and an expanded upper concavity - to - chord ratio.

[0272] Flow simulations also show that a similar increase in the global torque of the deflector / vane assembly, i.e., an increase in performance, can be achieved by (i) a smaller concavity in the pressure (upstream) surface of the deflector and a larger angle of attack between the deflector and the vane, and (ii) a larger concavity in the pressure (upstream) surface of the deflector and a smaller angle of attack between the deflector and the vane. The flow simulations further show that an increased concavity (i.e., a greater curvature or a greater recess depth 234, 248) or an increased angle of attack between the deflector and the vane results in an increased performance of the deflector / vane assembly.

[0273] The operating range of the lower protrusion 238 is less than that of the upper recess 230. The lower protrusion 238 affects the flow passing from the vane pressure surface side 178 to the deflector suction surface side 206 (in other words, from the upstream side of the vane 111 to the downstream side of the deflector 200) between the leading edge 208 of the deflector 200 and the trailing edge 174 of the vane. The flow simulations show that the flow passing through the opening between the deflector 200 and the vane 111 is an important variable for balancing the global torque and the type of torque (i.e., positive, negative, or neutral) attributable only to the deflector 200.

[0274] The flow simulations also show that changing the concavity / angle - of - attack ("AoA") relationship can also cause the deflector 200 to contribute positive or negative torque to the deflector / vane assembly. This is shown in the following table, which compares the representative blade torque, deflector torque, and global torque of a rotor blade without a deflector and a blade / deflector assembly, where, for comparison purposes, the torque values are normalized by the torque value obtained by the rotor blade alone. Three representative deflector configurations were compared: (i) a high deflector angle of attack (e.g., 13° - 15°) and a low concavity (e.g., 5% - 7% of the chord), (ii) a medium deflector angle of attack (e.g., 6° - 12°) and a medium concavity (e.g., 8% - 12% of the chord), and (iii) a low deflector angle of attack (e.g., 0° - 5°) and a high concavity (e.g., 13% - 20% of the chord).

[0275]

[0276] As shown in the above table, in this embodiment, adding the flow deflector increases the contribution of blade torque to the global torque, provided that the angle of attack and the recess depth are as described above in relation to the chord ratio. Additionally, as the angle of attack varies from high to low and the recess of the flow deflector varies from low to high, the contribution of blade torque to the global torque decreases, but the contribution of flow deflector torque to the global torque increases. In other words, compared to a blade without a flow deflector, a flow deflector configuration that results in a low or even negative torque contribution from the flow deflector results in a higher torque contribution from the blade, thus offsetting the low or negative flow deflector torque contribution to provide an increased global torque.

[0277] As Fig. 9C and Fig.9D shown, the flow deflector 200 has a flow deflector thickness 207 between the upstream surface 204 and the downstream surface 206, which can be constant from the flow deflector leading edge 208 to the flow deflector trailing edge 212. In one embodiment, the upstream surface 204 and the downstream surface 206 are flat and parallel. In other embodiments, the upstream surface 204 and the downstream surface 206 are curved and parallel (i.e., the upstream surface 204 and the downstream surface 206 are equidistant from the midline of the flow deflector thickness), and in other embodiments, the surfaces 204 and 206 are not parallel. In the case where the upstream surface 204 and the downstream surface 206 are curved and parallel, the rear recess 230 on the upstream surface 204 has a corresponding rear protrusion on the downstream surface 206, and the front protrusion 238 on the upstream surface 204 has a corresponding front recess on the downstream surface 206. In various embodiments, as Fig. 9C and Fig.9D shown, where the thickness of the flow deflector 200 is relatively small relative to the chord (e.g., the tip chord 224 - A and the hub chord 224 - E), the chord is at least partially outside the profile defined between the upstream surface 204 and the downstream surface 206, e.g., where the chord spans the rear recess 230 and / or the front protrusion 238.

[0278] 5.2 Flow Deflector / Blade Assembly Chord Details - Figure 9E-9J

[0279] Now referring to Fig.9E , a plan view of an exemplary embodiment of a blade / flow deflector assembly is shown, including a blade 111 and a flow deflector 200, and the pressure surface 178 of the blade 111 and the pressure surface 204 of the flow deflector 200 are shown. Details A, B, C, D, and E are transverse cross-sectional views of the blade / flow deflector assembly at sections A - A, B - B, C - C, D - D, and E - E, respectively.

[0280] The angle of blade chord 186-A-186-E (relative to rotor rotation plane 104 (see Figure 1A )) can be along the blade span 154 (see Figure 2A ) changes, as further described below.

[0281] The angle of the guide vane chord 224-A-224-E (relative to the rotor rotation plane 104 (see Figure 1A )) can be along the guide plate span 223 (see Fig.9A ) changes, as further described below.

[0282] Fig.9F yes Fig.9E FIG. 1 is an enlarged view of detail A and shows the tip end profile of the vane / guide plate assembly. Fig.9F The profile of the blade 111 has a chord line 196 extending from the blade leading edge 168 through the blade trailing edge 174 and a camber line 188 representing a line equidistant from the pressure surface 178 and the suction surface 182 . Fig.9F The deflector 200 profile has a chord line 258 extending from the leading edge 208 through the trailing edge 212 , and the deflector 200 profile includes a rear recess 230 .

[0283] Fig.9F The blade 111 profile is oriented at a blade angle of attack 194-A, and Fig.9F The deflector 200 profile is oriented at a deflector angle of attack 259-A.

[0284] Still reference Fig.9F , the leading edge 208 profile of the guide plate 200 is spaced apart from the blade trailing edge 174 profile of the blade 111 by a distance 228-A in a direction toward the oncoming fluid flow 1 (upstream).

[0285] Figure 9G yes Fig.9E Detail B is an enlarged view of the blade / baffle assembly and shows the profile of the blade / baffle assembly at a distance from the tip end that is twenty percent (20%) of the length of the span 154 of the blade 111 (see Figure 2A ). Figure 9G The profile of the blade 111 has a chord line 196 extending from the leading edge 168 through the blade trailing edge 174 and a camber line 188 representing a line equidistant from the pressure surface 178 and the suction surface 182 . Figure 9G The blade chord 186-B of the blade 111 profile (see Fig.9E The details B) may be different from (e.g., longer than) Fig.9F The blade chord 186-A of the blade 111 profile (see Fig.9E Details A). In addition, Figure 9G The camber line 188 of the blade 111 profile may be different from Fig.9F The mean camber line 188 of the blade 111 profile.

[0286] Figure 9G The profile of the deflector 200 has a chord line 258 extending from the leading edge 208 through the trailing edge 212 and includes a rear recess 230. Figure 9G The deflector chord 224-B of the profile of the deflector 200 (see Fig.9E Detail B) can be different from (e.g., longer than) Fig.9F The deflector chord 224-A of the profile of the deflector 200 (see Fig.9E Detail A). Figure 9G The curvature of the rear recess 230 of the profile of the deflector 200 can be different from Fig.9F The curvature of the rear recess 230 of the profile of the deflector 200.

[0287] Figure 9G The profile of the blade 111 is oriented at a blade angle of attack 194-B and can be different from Fig.9F The angle of attack 194-A due to blade twist.

[0288] Figure 9G The profile of the deflector 200 is oriented at a deflector angle of attack 259-B. Figure 9G The angle of attack 259-B of the profile of the deflector 200 can be different from Fig.9F The angle of attack 259-A of the profile of the deflector 200.

[0289] Figure 9G The leading edge 208 of the profile of the deflector 200 is spaced apart from the Figure 9G trailing edge 174 of the blade 111 profile by a distance 228-B in the direction towards the oncoming fluid flow 1 (upstream). Due to changes in vertical and / or horizontal skew (described below), Figure 9G the distance 228-B can be different from Fig.9F the distance 228-A.

[0290] Figure 9H is Fig.9E An enlarged view of Detail C. Figure 9H The profile of the blade 111 has a chord line 196 extending from the leading edge 168 through the trailing edge 174 and a mean camber line 188 representing the line equidistant from the pressure surface 178 and the suction surface 182. Figure 9H The chord 186-C of the profile of the blade 111 (see Fig.9E Detail C) can be different from (e.g., longer than) Fig.9F and Figure 9G the blade chords 186-A and 186-B of the profile of the blade 111 (see Fig.9E Detail A and Detail B) respectively. Additionally, Figure 9HThe mean camber line 188 of the blade 111 profile can be different from Fig.9F and Figure 9G the mean camber line 188 of the blade 111 profile.

[0291] Figure 9H The profile of the deflector 200 has a chord line 258 extending from the leading edge 208 through the trailing edge 212 and includes a rear recess 230. Figure 9H The chord 224-C of the profile of the deflector 200 (see Fig.9E detail C) can be different from (e.g., longer than) Fig.9F and 9G the deflector chords 224-A and 224-B of the profile of the deflector 200 (see Fig.9E detail A and detail B), respectively. Figure 9H The curvature of the rear recess 230 of the profile of the deflector 200 can be different from Fig.9F and Figure 9G the curvature of the rear recess 230 of the profile of the deflector 200.

[0292] Figure 9H The blade 111 profile is oriented at a blade angle of attack 194-C and, due to blade twist, can be different from Fig.9F the blade angles of attack 194-A of Figure 9G and

[0293] Figure 9H the blade angles of attack 194-B of Fig.9F and Figure 9G the deflector 200 profile is oriented at a deflector angle of attack 259-C and can be different from

[0294] Figure 9H the leading edge 208 of the profile of the deflector 200 is spaced apart from the trailing edge 174 of the Figure 9H blade 111 profile by a distance 228-C in the direction towards the oncoming fluid flow 1 (upstream). Due to changes in vertical and / or horizontal skew (described below), Figure 9H the distance 228-C can be different from Fig.9F the distance 228-A of Figure 9G and

[0295] Fig.9I is Fig.9E an enlarged view of detail D. Fig.9I The blade 111 profile has a chord line 196 extending from the leading edge 168 through the trailing edge 174 and a mean camber line 188 representing the line equidistant from the pressure surface 178 and the suction surface 182. Fig.9I The blade chord 186-D of the blade 111 profile (see Fig.9EThe details D) can be different from (e.g., longer than) Fig.9F , Figure 9G and Figure 9H the blade chords 186-A, 186-B, 186-C of the blade 111 profile (see details A, B, and C of Fig.9E respectively). Additionally, Fig.9I the mean camber line 188 of the blade 111 profile can be different from Fig.9F , Figure 9G and Figure 9H the mean camber line 188 of the blade 111 profile.

[0296] Fig.9I The profile of the deflector 200 has a chord line 258 extending from the leading edge 208 through the trailing edge 212 and includes a rear recess 230. Fig.9I The deflector chord 224-D of the profile of the deflector 200 (see Fig.9E detail D) can be different from (e.g., longer than) Fig.9F , Figure 9G and Figure 9H the deflector chords 224-A, 224-B, 224-C of the profile of the deflector 200 (see details A, B, and C of Fig.9E respectively). Fig.9I The curvature of the rear recess 230 of the profile of the deflector 200 can be different from Fig.9F , Figure 9G and Figure 9H the curvature of the rear recess 230 of the profile of the deflector 200.

[0297] Fig.9I The profile of the blade 111 is oriented at a blade angle of attack 194-D and, due to blade twist, can be different from Fig.9F the blade angle of attack 194-A of Figure 9G the blade angle of attack 194-B of Figure 9H and the blade angle of attack 194-C of

[0298] Fig.9I The profile of the deflector 200 is oriented at a deflector angle of attack 259-D and can be different from Fig.9F , Figure 9G and Figure 9H the angles of attack 259-A, 259-B, and 259-C of the profile of the deflector 200.

[0299] Fig.9I The leading edge 208 of the profile of the deflector 200 is spaced apart from the trailing edge 174 of the profile of the Fig.9I blade 111 by a distance 228-D in the direction towards the oncoming fluid flow 1 (upstream). Due to changes in vertical and / or horizontal skew (described below), Fig.9IThe distance 228-D can be different from Fig.9F the distance 228-A, Figure 9G the distance 228-B, and Figure 9H the distance 228-C.

[0300] Figure 9J is Figure 9E an enlarged view of detail E and shows the hub end profile of the blade / vane assembly. Figure 9J The profile of the blade 111 has a chord line 196 extending from the leading edge 168 through the trailing edge 174 and a mean camber line 188 representing the line equidistant from the pressure surface 178 and the suction surface 182. Figure 9J The blade chord 186-E of the profile of the blade 111 (see Figure 9E detail E) can be different from (e.g., longer than) Figure 9F , Figure 9G , Figure 9H and Figure 9I the blade chords 186-A, 186-B, 186-C, and 186-D of the profile of the blade 111 (see details A, B, C, and D respectively in Figure 9E detail A, detail B, detail C, and detail D). Additionally, Figure 9J the mean camber line 188 of the profile of the blade 111 can be different from Figure 9F , Figure 9G , Figure 9H and Figure 9I the mean camber line 188 of the profile of the blade 111.

[0301] Figure 9J The profile of the vane 200 has a chord line 258 extending from the leading edge 208 through the trailing edge 212 and includes a rear recess 230. Figure 9J The vane chord 224-E of the profile of the vane 200 (see Figure 9E detail E) can be different from (e.g., longer than) Figure 9F , Figure 9G , Figure 9H and Figure 9I the vane chords 224-A, 224-B, 224-C, and 224-D of the profile of the vane 200 (see details A, B, C, and D respectively in Figure 9E detail A, detail B, detail C, and detail D). Figure 9J The curvature of the rear recess 230 of the profile of the vane 200 can be different from Figure 9F , Figure 9G , Figure 9H and Figure 9I the curvature of the rear recess 230 of the profile of the vane 200.

[0302] Figure 9J The profile of the blade 111 is oriented at a blade angle of attack 194-E and can be different from, due to blade twist,Figure 9F angle of attack 194 - A, Figure 9G angle of attack 194 - B, Figure 9H angle of attack 194 - C and Figure 9I angle of attack 194 - D.

[0303] Figure 9J The profile of the deflector 200 is oriented at a deflector angle of attack 259 - E and can be different from the Figure 9F , Figure 9G , Figure 9H and Figure 9I angles of attack 259 - A, 259 - B, 259 - C, and 259 - D of the profile of the deflector 200.

[0304] Figure 9J The leading edge 208 of the profile of the deflector 200 is spaced apart from the trailing edge 174 of the profile of the vane 111 by a distance 228 - E in the direction towards the oncoming fluid flow 1 (upstream) and Figure 9J due to changes in vertical and / or horizontal skew (described below), Figure 9J the distance 228 - E can be different from the Figure 9F distance 228 - A, Figure 9G distance 228 - B, Figure 9H distance 228 - C, and Figure 9I distance 228 - D.

[0305] 6. Fixed connectors and related structures - Figures 9K - 9N

[0306] Now referring to Figure 9K , an embodiment of the deflector 200 is fixedly linked to the suction side 182 of the vane 111 via one or more connector assemblies (or connector brackets) 261. As Figure 9M shown, in one embodiment, the connector assembly 261 includes a deflector end flange 271, a vane end flange 272, and a connector tube 270. The connector assembly 261 is attached to the deflector 200 at the deflector end flange 271, the connector assembly 261 is attached to the rotor vane 111 at the vane end flange 271, and the connector tube 270 extends between and connects the vane end flange 272 and the deflector end flange 271. The flange 272 may have one or more holes 286 for fasteners that are used to fixedly link the assembly 261 to a structural member within the vane 111, as described below.

[0307] In one embodiment, as Figure 9K and Figure 9L shown, the connector assembly 261 has a longitudinal shape between the rotor vane 111 and the deflector 200 that follows its rotation about the rotor axis 123 (see Figure 1A) The corresponding travel path 275 of the rotation 5 (i.e., each connector assembly 261 conforms to an arc centered on the rotor rotation axis 123 (see Figure 1A ) and having a radius corresponding to the spanwise position of the connector assembly)). In the illustrated embodiment, as Figure 9L shown, the connector tube 270 is shaped to conform to the travel path 275 between the connecting vane end flange 272 and the deflector end flange 271 (see Figure 9M ). Other embodiments of the deflector connector assembly may have different longitudinal shapes.

[0308] The connector assembly 261 includes two sets of leading and trailing edges; one set of leading and trailing edges minimizes the drag caused by the oncoming fluid flow, and the second set of leading and trailing edges minimizes the drag caused by the rotating fluid flow and the apparent velocity 6. These two sets of edges are described further below.

[0309] Figure 9L is an enlarged cutaway rear view of the deflector / vane assembly, showing a portion (i.e., the tube 270) of a single connector assembly 261 extending between the vane 111 and the deflector 200.

[0310] Now referring to Figure 9L and Figure 9L of detail A and Figure 9M and Figure 9M of detail A, the connector assembly 261 includes a rotating flow leading edge 276 and a rotating flow trailing edge 278, which are oriented to align with the rotating flow and can be oriented according to the designer's choice of any particular RPM. That is, as shown, the tube 270 extends substantially from the deflector 200 and the vane 111 into the apparent velocity fluid flow 6 through the downstream surfaces 206 and 182. Due to the curvature of the outer edge of the tube 270 (i.e., the edge farthest from the downstream surfaces 206 and 182), the apparent velocity fluid flow 6 first contacts the portion 276 of the outer edge of the tube 270, flows around the tube 270, and then flows past the portion 278 of the outer edge of the tube 270. The leading edge 276 begins at the point closest to the oncoming rotating flow and then the apparent velocity fluid flow 6, and ends at the vertex 277 of the curvature of the tube 270 (see Figure 9M and Figure 9L of detail A). The rotating flow trailing edge 278 begins at the vertex 277 and ends at the point on the connector assembly 261 closest to the deflector trailing edge 212.

[0311] Now referring to Figure 9M of detail A, which is a cross-section along the line A-A in Figure 9M , while still referring to Figure 9L, A longitudinal section of the connector assembly 261 reveals an oval shape of an embodiment of the tube 270. A cross-section A-A of the tube 270 may have an aerodynamic shape with tapered ends to a leading edge 276 and to a trailing edge 278, and may be laterally symmetric about a line bisecting the section between the leading edge 276 and the trailing edge 278. Exemplary shapes may include oval, pointed dome, spherical blunt pointed dome, or parabola, and other similar shapes.

[0312] Now referring to Figure 9L detail A, the longitudinal shape of the connector assembly 261 follows an arcuate shape of a rotational path 275 traveling from the leading edge 276 to the trailing edge 278.

[0313] Now referring to Figure 9M detail B, which is a cross-section along line B-B in Figure 9M while still referring to Figure 9M , the tube 270 has a leading edge 273 oriented towards the oncoming fluid flow 1 and an opposite trailing edge 274. The tube 270 is oriented relative to the blade 111 and the deflector 200 such that when the blade / deflector assembly is in a stationary, non-rotating state, the oncoming fluid flow 1 flows around the tube 270 from the leading edge 273 to the trailing edge 274. A cross-section B-B of the tube 270 may have an aerodynamic shape with tapered ends to the leading edge 273 and to the trailing edge 274, and may be laterally symmetric about a line bisecting the section between the leading edge 273 and the trailing edge 274. Exemplary shapes may include oval, pointed dome, spherical blunt pointed dome, or parabola, and other similar shapes.

[0314] Thus, the tube 270 defines two sets of leading and trailing edges, a leading edge 273 and a trailing edge 274 relative to the oncoming fluid flow impinging on the stationary blade deflector assembly, and a leading edge 276 and a trailing edge 278 relative to the apparent fluid flow impinging on the rotating blade deflector assembly. The leading edge 273, trailing edge 274, leading edge 276, and trailing edge 278 of the connector tube 270 (collectively referred to as "connector tube edges") reduce drag, for example, by reducing the drag coefficient, i.e., a tapered edge has a lower drag coefficient than a square edge. Note that the trailing edge 274 includes both the leading edge 276 and the trailing edge 278. The geometry of the tube 270 may be varied such that its cross-section is more favorable for low speed - whereby the leading edge 273 and the trailing edge 247 are more tapered, or for high speed, where the leading edge 276 and the trailing edge 278 are more tapered.

[0315] Now referring to Figure 9N, in one embodiment, the leading edge 208 of the fairing 200 is positioned near the trailing edge 174 of the blade. The fairing end flange 271 is connected to the fairing 200 (e.g., by mechanical fasteners (screws, bolts, rivets), adhesives, welding, co - molding, interlayer lamination, or some combination thereof) such that the flange 271 is preferably embedded within the thickness of the fairing 200 between the upstream surface 204 and the downstream surface 206. The blade end flange 272 is fixedly linked to the U - shaped webs 116 and 117 within the blade 111 via fasteners 287. In another embodiment, the fairing - to - blade connector can be fixedly linked externally to the fairing 200 and / or the blade 111. The stiffeners 114 and 115 are fixedly linked within the blade 111 and reinforce the blade 111 where the blade 111 is fixedly linked to the webs 116 and 117. The webs 116 and 117 and the stiffeners 114 and 115 can extend along any length of the blade span 154 (see Figure 2A ).

[0316] The connector assembly 261 conforms to the twist of the fairing / blade assembly and the camber of the fairing 200, and thus the (i) twist and / or (ii) length or angle of the connector assembly 261 can vary along the fairing span 223 (see Figure 9A ).

[0317] 7. Operating Principle, Flow Simulation Results, and Physical Test Results

[0318] The pressure units in the figures cited in this section are expressed in Pascals (Pa).

[0319] The fairing 200 increases and decreases the pressure and / or velocity on the blade 111 as needed (see Figure 2A and Figure 2B ), resulting in an increase in positive torque on the blade 111 that benefits from the fairing 200 compared to a similar blade 111 without the benefits of the fairing 200. Thus, the blade 111 that benefits from the fairing 200 has a higher global torque at a given fluid velocity than a similar blade operating under the same conditions without a fairing. For example, a blade with a fairing operating at a wind speed of 8 miles per hour has a performance similar to that of a similar blade without a fairing operating at a wind speed of 11 miles per hour.

[0320] The cross - sectional views and isometric views of the blades and fairing / blade assemblies mentioned in this section, as well as the graphs included in the reference drawings, are obtained from flow simulations and are related to the performance data observed during physical testing of a scaled physical model. The CAD model diameter of the rotor used in this section is 93 meters. The pressures and suctions recorded in the cross - sectional views and isometric views in this section were measured at a distance of 41.66 meters from the rotor rotation axis 123 (see Figure 1).

[0321] 7.1 Fluid flow and pressure before rotation - Figures 10A - 10F

[0322] Figure 10A is a side view of a cross - section of the stationary non - rotating blade 111 without the deflector 200 and shows the flow path lines around the blade 111. Figure 10B is a side view of a cross - section of the stationary non - rotating deflector / blade assembly including the blade 111 and the associated deflector 200 and shows the flow path lines around the deflector / blade assembly. Figure 10A and Figure 10B the velocity of the fluid flow 1 in Figure 1B and Figure 1A is so low (e.g., 2.0 m / s) that the blade 111 does not start to rotate due to mechanical resistance (e.g., due to the generator 128 (see

[0323] Now referring to Figure 10A , the fluid flow 1 impinging on the pressure surface 178 of the blade 111 exhibits a pressure - side transition point 2 - A at a distance 16 - A from the trailing edge 174 of the blade. The transition point 2 - A is where the oncoming fluid flow 1 separates, where (i) a portion 3 - A of the fluid flow is pushed towards the trailing edge 174 of the blade 111 and accelerates around the trailing edge 174 of the blade 111 (upward in the illustration), and a portion 4 - A of the fluid flow is pushed towards and accelerates around the leading edge 168 of the blade 111 (downward in the illustration). The fluid flow 4 - A moving windward past the leading edge 168 results in a low pressure on the suction side 182 and a desired positive torque 7 - A. The fluid flow 3 - A moving windward on the trailing edge 174 results in a low pressure on the suction side 182 and an undesired negative torque 8 - A.

[0324] Now referring to Figure 10B , and still referring to Figure 10A , the deflector 200 deflects a portion of the oncoming fluid flow 1 that would otherwise pass behind the trailing edge 174 of the blade (above in the illustration) without impinging on the blade 111, and causes a portion of the oncoming fluid flow 1 that would impinge on the blade near its trailing edge 174 (independent of the deflector 200) to flow towards (downward in the illustration) and around the leading edge 168 of the blade. The deflected flow results in (i) a greater volume of fluid passing through the blade pressure surface 178, including towards and past the leading edge 168, and thus across the suction surface 182, and thus (ii) increasing and decreasing the pressure as needed on the beneficial regions of the pressure surface 178 (see sub - sections 1.2 and 1.3), and (iii) increasing and decreasing the suction as needed in the beneficial regions of the suction surface 182 (see sub - sections 1.2 and 1.3).

[0325] The increased flow volume flowing around the leading edge 168 of the blade 111 increases the pressure between the transition point 2-B and the trailing edge 174 of the blade (see beneficial region 16 - see Figure 2G ). The increase in volume and pressure results in: (i) the pressure side transition point 2-B of the deflector / blade assembly moves closer to the trailing edge 174 of the blade compared to the transition point 2-A, thereby reducing the distance 16-B between the transition point 2-B and the trailing edge 174 of the blade compared to the distance 16-A in Figure 10A , (ii) the smaller fluid flow 3-B of the oncoming fluid flow 1 is pushed towards and around the trailing edge 174 of the blade, thereby reducing the harmful suction and negative torque in the beneficial region 16 (see Figure 2G ), and (iii) the larger fluid flow 4B is pushed towards and around the leading edge 168 of the blade compared to the fluid flow 4A in Figure 10A , thereby increasing the suction in the beneficial region 14 on the suction side 178 of the blade (see Figure 2G ).

[0326] Figure 10B The additional fluid flow 4-B on the pressure side 178 of the blade 111 of the deflector / blade assembly is mixed by the oncoming fluid flow 1 and pushed past the leading edge 168 of the blade, thereby reducing the pressure on the suction side 182 of the blade 111 between the transition point 2-B and the leading edge 168 compared to the blade 111 without the benefits of the deflector 200 (see Figure 10A , i.e., compared to a blade with less fluid flow 4-A around the leading edge 168).

[0327] Thus, the additional flow volume from the deflector 200 results in (i) a reduction in harmful suction and negative torque 8-B compared to 8-A, (ii) an increase in desired suction and a greater positive torque 7-B compared to 7-A, and (iii) an increase in the global torque on the blade 111 with the benefits of the deflector 200 ( Figure 10A ) compared to the blade 111 without the benefits of the deflector 200 ( Figure 10B ).

[0328] Figure 10C is Figure 10A a side view of the pressure curve around the blade surface of the blade, and Figure 10D is Figure 10B a side view of the pressure curve around the blade and the deflector surface of the deflector / blade assembly. Now referring to Figure 10C and Figure 10D , when comparing the two pressure diagrams, the performance improvements seen in the pressure are visible and are very significant near the trailing edge 174 of the blade on the suction side 182 of the blade (see Figure 10C and Figure 10D ), where inFigure 10C The minimum pressure of -4.09 Pa on blade 111 without the benefit of the flow deflector 200 (pressure region -4.09–-1.72 Pa) has decreased by more than 2.5 times to Figure 10D -1.42 Pa in Figure 10C and Figure 10D . It is important to note that the performance improvements shown in the graphs ( Figure 9E ) occur near the blade tip end 151 where the moment arm is the longest (see detail A in Figure 9E ), thus helping the blades benefiting from the flow deflector to start rotating faster and at a lower fluid velocity than those not benefiting from the flow deflector.

[0329] The above-mentioned 93-meter CAD model and subsequent flow analysis results were scaled down by 146.4 times, and its chord was truncated by three percent (3%) to accommodate 3D printing technology. The physical diameter is 25 inches. Its performance was measured with redundant sensors, all with the same results, and recorded with a programmable logic controller. Comparing the physical test performance data samples of the scaled model rotors with blades with and without flow deflectors, both rotors were under the same load (drag) of 0 - 15.5 m / s. The results for 0 - 2.68 m / s are included in the following table. As shown by the test data, for the rotor with blades with flow deflectors, the rotor rotation starts at a lower wind speed, and for the rotor with blades with flow deflectors, the rotor rotation is higher at the same wind speed.

[0330]

[0331] Now refer to Figure 10E and Figure 10F , which are enlarged side isometric views of Figure 10A and Figure 10B respectively, showing the surface pressures on the upstream and downstream surfaces of the cross-section, and where the pressure regions are shown on the outer side of the upstream surface and the inner side of the downstream surface. Significant performance improvements can be seen on the suction surface 182 of blade 111. For example, the narrow cross-hatched portion of the suction surface of blade 111 benefiting from the flow deflector 200 (see Figure 10F ) has a lower pressure amplitude (-1.37 - 1.32 Pa) than the suction surface of the blade not benefiting from the flow deflector 200 (with a pressure amplitude of -1.67 - 1.62 Pa (see Figure 10E ), and in the beneficial region 16 (see Figure 2G ), the lower pressure has a performance benefit as this is the region where negative torque is generated.

[0332] 7.2 Fluid flow and pressure during rotation at 3.5 m / s -Figures 11A - 11J

[0333] The figures in this subsection depict the results of a flow simulation from a rotor with a diameter of 93 meters, at an oncoming fluid flow velocity of 3.5 m / s, rotating about the rotor axis 123 of rotor 110 (see Figure 1A ) at a desired counterclockwise rotation 5 (downward in the illustration) at 4.3 RPM. The center of the sectional view and the isometric view shows the results obtained at a distance of 41.66 meters from the rotor axis 123 (see Figure 1A ). At such a distance from the hub axis, the center of the sectional view and the isometric view in this subsection rotates at a circumferential velocity of 18.8 m / s.

[0334] Figure 11A is a side view of a cross-section of the rotating blade 111 without a deflector, which shows the apparent velocity flow trajectory lines around the pressure (upstream) surface 178 and the suction (downstream) surface 182 of the blade. Figure 11B is a side view of a cross-section near the blade tip of the rotating deflector / blade assembly including the blade 111 and the deflector 200 as described above, which shows the apparent velocity flow trajectory lines around the pressure (upstream) surface 178 and the suction (downstream) surface 182 of the deflector / blade assembly and the representative pressure regions. Although it is expected that Figure 11B the blades in Figure 11A will rotate faster than the blades in

[0335] Now referring to Figure 11A , the fluid flow from the apparent velocity 6 separates as it approaches the leading edge 168 of the blade, where the fluid flow 7-A passes near the pressure side 178 of the blade 111, and the fluid flow 8-A accelerates near the suction side 182 of the blade 111. The pressure difference between the pressure side 178 and the suction side 182 and its interaction with the geometry of the blade 111 cause the blade 111 to rotate at the desired counterclockwise rotation 5.

[0336] Now referring to Figure 11B , while still referring to Figure 11AWhen the apparent velocity 6 approaches the blade leading edge 168, its separation pattern is different from that without the benefit of the flow deflector 200, where a greater amount of the apparent velocity 8-B passes near the blade suction side 182. This difference is caused by the flow deflector 200 creating a high-pressure region 19 on the upstream side of the flow deflector 200 and a high-speed low-pressure region 20 on the downstream side of the flow deflector 200, which counteracts the drag generated by the high-pressure region 19, as further described below.

[0337] High-pressure region 19: (i) increases in size and magnitude due to the oncoming fluid flow 1 impinging on the flow deflector 200 and would not otherwise affect the performance of the blade 111 if the blade 111 did not benefit from the flow deflector 200, (ii) significantly increases the pressure (increase in size and magnitude) in the region 21 adjacent to the blade pressure surface 178 in the beneficial region 10 (see Figure 2G ), and thus increases the fluid flow 8-B and positive torque on the blade suction surface 182 by redirecting more of the apparent velocity fluid flow 6 onto the blade suction surface 182, as compared to 8-A in Figure 11A , (iii) slows down the apparent velocity of the fluid flow 7-B as the fluid flow 7-B approaches and passes through the blade pressure side 178, and (iv) reduces the volume and velocity of the fluid flow 7-B adjacent to the blade recess 180 (also see the details A-C in Figure 2A ), as compared to the blade 111 without the benefit of the flow deflector 200 in Figure 11B , which together result in positive torque on the pressure surface 178 and an increase in the global torque on the blade 111, while the blade 111 without the benefit of the flow deflector 200 in Figure 11B has negative torque on its pressure surface 178 and negative torque on the pressure surface without the benefit of the flow deflector 200 in Figure 11B .

[0338] The high-pressure region 21 on the pressure surface 178 of the blade 111 causes a greater portion of the apparent velocity 6 approaching the blade leading edge 168 to change direction and flow over the suction surface 182 rather than the pressure surface 178 (which would typically cause additional drag on the pressure surface 178 in the beneficial region 11 (see Figure 2G ), thus converting the undesired pressure-side 178 drag near the blade leading edge 168 into a desired suction-surface 182 force, where it benefits performance by increasing positive torque. The high-pressure region 21 also causes the apparent velocity fluid flow 6 to accelerate at a higher speed adjacent to the suction surface 182. The increased flow at a higher speed on the suction surface 182 results in a greater suction force from the leading edge 182 through the beneficial region 15 (see Figure 2G ), and thus a greater positive torque on the suction side 182 of the blade 111 than on the blade 111 without the benefit of the flow deflector 200.

[0339] Now refer to Figure 11C and Figure 11D , the performance improvement is an example of a beneficial pressure change along the blade span 154 (see Figure 2A ). For example, now refer to Figure 11C , (i) the pressure on the beneficial area 10 (see Figure 2G ) of the pressure side 178 of the blade is 100 - 123 Pa on the blade 111 without the deflector 200, in contrast, it is 100 - 150 Pa on the blade 111 with the benefit of the deflector 200, and covers a surface area more than 1.5 times that of the beneficial area 10 (see Figure 2G ), and (ii) the suction on the suction side 182 near the leading edge of the blade 111 is -520 - -250 Pa in the beneficial area 14 without the benefit of the deflector 200 (see Figure 2G ), in contrast, it is -1006 - -250 Pa on the blade 111 with the benefit of the deflector 200 (see Figure 11D ). Therefore, both the pressure side 178 and the suction side 182 of the blade generate a greater positive torque due to the deflector 200.

[0340] Now refer to Figure 11E and Figure 11F , the benefit of the deflector 200 on the pressure surface 178 in a 3.5 m / s wind along the blade span 154 (see Figure 2A ) is evident. For example, without the benefit of the deflector 200 (see Figure 11E ), the pressure on the rear recess 180 on approximately twenty-eight (28%) of the blade 111 span 154 (see Figure 2A ) is 100 - 150 Pa, in contrast, with the benefit of the deflector 200 (see Figure 11F ), it is 100 - 150 Pa on at least seventy-nine (79%) of the blade 111 span 154 (see Figure 2A ). In addition, Figure 11F the higher pressure shown is in a more favorable region due to its increased slope angle on the blade (see subsection 1.2), that is, the region in the blade geometry where the pressure difference is beneficial to the blade (rotor) performance. The deflector 200 is not shown in the pressure curves shown in Figure 11F , Figure 11H and Figure 11J (see Figure 9A ).

[0341] Now refer to Figure 11G and Figure 11H , the benefit of the deflector 200 on the suction (downstream) surface 182 in a 3.5 m / s wind along the blade span 154 (see Figure 2A) occurs. For example, in the absence of the benefits of the deflector 200, the suction on the suction side 182 of the blade 111 near the tip and near the leading edge 168 is -956--300 Pa (see Figure 11G ), whereas, in the presence of the benefits of the deflector 200, the suction on the blade near the tip and near the leading edge is -1865--300 Pa (see Figure 11H ), and the maximum suction is almost doubled. In addition, by comparing Figure 11G and Figure 11H it can be seen that, in the presence of the deflector ( Figure 11H ), the area on the suction surface where the pressure is -1865–-300 Pa is more than three times the size of the area on the suction surface where the pressure is -956–-300 Pa in the absence of the deflector ( Figure 11G ).

[0342] Now refer to Figure 11I and Figure 11J , which are respectively enlarged side isometric views of section 11I of Figure 11E and Figure 11G and section 11J of Figure 11F and Figure 11G , showing the surface pressures on the corresponding pressure and suction surfaces.

[0343] In the absence of the benefits of the deflector 200 (see Figure 11I ), for the same wind speed, the benefits of the deflector 200 on the upstream and downstream surfaces of the section of the blade 111 in a 3.5 m / s wind (see Figure 11J ) are shown on the section of the blade 111. For example, on the blade 111 in the absence of the benefits of the deflector 200 (see Figure 11I ), the pressure on most of the pressure surface 178 shown with wide cross-hatching is 50 Pa - 100 Pa, in a region with a small slope angle, and thus the beneficial part of region 10 is small (see subsections 1.2 - 1.3), whereas, on the blade 111 with the benefits of the deflector 200 (see Figure 11J ), the pressure shown in the wide cross-hatching region on the pressure surface 178 is 100 Pa - 150 Pa, entirely in the beneficial region and with a larger slope angle (see subsections 1.2 - 1.3). Similarly, on the blade 111 in the absence of the benefits of the deflector 200 ( Figure 11I ), the suction on the suction side 182 shown with narrow cross-hatching is -710--250 Pa, whereas, on the blade 111 with the benefits of the deflector 200 ( Figure 11J) is shown as -1308--250 Pa in the narrow cross-hatched area on the suction surface 182, and in a larger beneficial area (see subsections 1.2 - 1.3). Since the deflector 200 generates a higher positive torque due to the increased negative pressure on the suction side 182 near the leading edge 168, it further increases the performance improvement seen on the blades that benefit from the deflector 200.

[0344] The following table shows additional examples of the performance improvement achieved by comparing common points on the pressure surface 178 and the suction surface 182 of blade 111 between a blade without a deflector and a blade with a deflector. However, it is important to note that the pressure side 182 of blade 111 has areas that ideally benefit from pressure and other areas that ideally benefit from suction. Similarly, the suction side 182 of blade 111 has areas that ideally benefit from suction and other areas that ideally benefit from pressure (see subsections 1.2 and 1.3). The following chart includes the required pressure type, low pressure (suction) or high pressure, of the measurement points.

[0345]

[0346] The physical test results at 3.5 m / s are as follows:

[0347]

[0348] The performance of the deflector is similar, but as the fluid velocity increases, the improvement becomes even more apparent, as further described below.

[0349] 7.3 Fluid flow and pressure during rotation at 13 m / s - Figures 12A - 12H

[0350] When rotating at all fluid velocities, the deflector similarly affects the flow. Therefore, the explanation in the previous subsection of how the deflector works applies to this subsection. Additionally, since the kinetic fluid energy is proportional to the square of the fluid velocity, the deflector performance improves exponentially with increasing velocity. Furthermore, regardless of the fluid velocity, when the deflector / blade assembly rotates, the flow trajectory and pressure curve are similar. However, the higher the fluid velocity, the significantly higher the pressure, suction, and global torque performance metrics.

[0351] The figures in this subsection depict the results of a flow simulation from a rotor with a diameter of 93 meters, studied in an oncoming fluid flow 1 of 13 m / s, rotating about the rotor axis of rotation 123 at 16 RPM (see Figure 1A ) rotating in a desired counterclockwise direction 5 (downward in the illustration). The center of the cross-sectional view and the isometric view shows at a distance from the rotor axis of rotation 123 (see Figure 1A)Results obtained at a distance of 41.66 m. At such a distance from the axis of rotation of the rotor 123, the center of the sectional view and the isometric view in this subsection rotates at a circumferential speed of 69.8 m / s. Also, for the purpose of flow analysis, the blades with and without the flow deflector rotate at the same speed. Therefore, physical tests show that the results of the blade / flow deflector combination reported herein are underestimated.

[0352] Now refer to Figure 12A and Figure 12B , the oncoming fluid flow 1 is 13 m / s, and the blade 111 rotates about the axis of rotation of the rotor 123 (see Figure 1A ) in the desired counterclockwise rotation (downward in the figure).

[0353] As described in the previous paragraph, the performance improvement at a distance of 41.66 m from the hub axis is an example of the beneficial pressure change along the span 154 (see Figure 2A ). For example, (i) the pressure on the rear recess 180 (see Figure 12A ) on the blade 111 without the benefit of the flow deflector 200 (see Figure 12C , detail A) is 1200 - 1800 Pa, while for the blade 111 with the benefit of the flow deflector 200 (see Figure 12B ), the pressure on a large part of the recess is 1800 - 2400 Pa, and (ii) the maximum suction on the suction side 182 near the leading edge on the blade 111 without the benefit of the flow deflector 200 is -6739 Pa, while for the blade with the benefit of the flow deflector (see Figure 12B ) it is -13,032, Figure 12B the increased suction on the suction side 182 of the blade in Figure 2A is over an area more than twice as large and near the blade tip 151 where the moment arm is greatest, as described above.

[0354] Now refer to Figure 12C and Figure 12D , on the pressure surface 178, in a 13 m / s wind, the benefit of the flow deflector 200 along the blade span 154 (see Figure 2A ) is evident. For example, without the benefit of the flow deflector 200 (see Figure 12C ), the pressure on the rear recess 180 is 0 - 1200 Pa over more than 58% of the blade 111 span 154 (see Figure 2A ), while with the benefit of the flow deflector 200 (see Figure 12D ), it is 1200 - 2400 Pa over more than 87% of the blade 111 span 154 (see Figure 2A ). Additionally, Figure 12DThe higher pressure shown in [Figure] is in a more favorable region due to its increased slope angle on the blade (see subsection 1.2), i.e., the region in the blade geometry where the pressure difference is beneficial to the blade (rotor) performance. In Figure 12D and Figure 12F and Figure 12H the deflector 200 is not shown in the pressure curves shown (see Figure 9A ).

[0355] Now referring to Figure 12E and Figure 12F , the benefit of the deflector 200 on the suction surface 182 in a 13 m / s wind is evident along the span 154 (see Figure 2A ). For example, the suction on the suction side 182 near the tip and near the leading edge on the blade 111 without the benefit of the deflector 200 is -12,442 - -2400 Pa (see Figure 12E ), whereas on the blade with the benefit of the deflector 200 the suction is -23,431 - -2400 Pa (see Figure 12F ), almost doubling the suction over an area more than 3 times as large.

[0356] Now referring to Figure 12G and Figure 12H , these two figures are respectively enlarged side isometric views of section 12G of Figure 12C and Figure 12E and section 12H of Figure 12D and Figure 12F , showing the surface pressures on the corresponding pressure surface and suction surface. The benefit of the deflector on the upstream and downstream surfaces of the section of the blade 111 in a 13 m / s wind is evident on the section of the blade 111 at the same wind speed. For example, (i) on the blade 111 without the benefit of the deflector 200 (see Figure 12G ), the pressure on most of the pressure surface 178 represented by wide cross-hatching is 600 Pa - 1200 Pa, whereas on the blade 111 with the deflector 200 the pressure shown in the area of wide cross-hatching on the pressure surface 178 is 1800 Pa - 2400 Pa (see Figure 12H ), and (ii) on the blade 111 without the benefit of the deflector 200, the suction shown by narrow cross-hatching on the suction side 182 is -9382 - -3000 Pa ( Figure 12G ), whereas on the suction surface 182 of the blade 111 with the benefit of the deflector 200, -17,139 - -3000 Pa is shown in the area of narrow cross-hatching ( Figure 12H ).

[0357] The physical test results at 3.5 m / s are as follows:

[0358]

[0359] In the illustrated embodiment, the global torque of the deflector / vane assembly is significantly greater than that of the vane 111 in the absence of the benefits of the deflector 200. Regardless of the torque of the vane 111, the additional positive, negative, or neutral torque attributable to the deflector 200 can be positive, negative, or neutral, as described in Section 8.

[0360] 8. Optimization Parameters - Figures 13A - 13E

[0361] The deflector / vane performance is affected by the interrelationships of many deflector parameters, including (i) overall shape and size, (ii) angle of attack, (iii) position relative to the vane, (iv) trailing concave length and depth, leading convex length and depth, and (v) vertical and horizontal skew (collectively referred to as "optimization parameters"). Alternative embodiment features of the deflector include but are not limited to suction side deflectors, deflector profiles of non-uniform thickness (e.g., common airfoil shapes), leading edge curved tips, leading edge arced tips, fluid walls, and the number of deflectors (collectively referred to as "alternative embodiment features").

[0362] Flow simulations and physical tests in each case where they have been performed indicate that the optimization parameters can be adjusted to obtain increased vane performance at (i) a given fluid velocity range and (ii) a specific fluid velocity, both of which also increase vane performance over the entire operating velocity range. Since the deflector changes the environment in which the vane operates, and vanes of different rotor sizes and manufacturers have different geometries, the optimization parameters can be used to improve the performance of unique vane designs to which the deflector can be customized and attached.

[0363] The optimization parameters can also be used when adding one or more alternative embodiments to the deflector (e.g., arced tips (see Subsection 9.4) and fluid walls (see Subsection 9.5)). When any one or more alternative embodiments are added to a given deflector embodiment, the optimization parameters can be used to change the peak performance of a given vane / deflector assembly, e.g., customized for a specific fluid velocity, due to the interrelationship between the deflector and the vane.

[0364] Based on combinations of the optimization parameters, an increase in global torque can be achieved in a variety of ways and with different results. For example, many flow simulations indicate that if the deflector has a large negative torque, the greatest global torque improvement can be achieved. However, as shown in Section 7, a smaller negative deflector torque, positive deflector torque, or neutral deflector torque may be more desirable at the expense of a smaller but significant increase in global torque.

[0365] In this section, when the deflector 200 is located on the suction side of the blade, all illustrations of the deflector 200 and related features share the same numerical part of the part number, however, with "-S" appended.

[0366] 8.1 Angle of attack and position relative to fluid flow - Figures 13A - 13B

[0367] For ease of understanding the content described in this subsection, (i) the rotor rotation plane 104 and the blade chord 186 are collinear, and (ii) the angle of attack of the deflector 200-S is exaggerated to aid in presenting the subject matter. Figure 13A and Figure 13B Each shows two deflectors, each at the same relative distance above the blade (i.e., behind the blade relative to the direction of rotation), and each deflector is oriented at the same relative angle of attack. Figure 13A The deflectors in Figure 13B are all further away from the oncoming flow 1 than the deflectors shown in

[0368] Figure 13A and Figure 13B are used to describe details regarding (i) the position of the deflector 200 when the leading edge of the deflector 200 is closer to the oncoming fluid flow 1 than the trailing edge 174 of the blade, (ii) the distance by which the leading edge 208-S of the deflector 200-S is behind the trailing edge 174 of the blade, (iii) the ability to have both the deflector 200 and the deflector 200-S in one embodiment, and (iv) the characteristic of advancing the deflector towards the oncoming flow while maintaining its angle of attack. In all the figures cited in this subsection, the pressure side of the deflector and the blade is located in the position closest to the oncoming flow.

[0369] Now referring to Figure 13A , an embodiment is shown where the profile of the deflector 200 is closer to the oncoming fluid flow 1 than the profile of the blade 111 (i.e., the deflector 200 is upstream of the blade 111, so the fluid flow 1 strikes the deflector 200 before it strikes the blade 111) and the second deflector profile 200-S is further away from the oncoming fluid flow 1 than the blade profile 111 (i.e., the deflector 200-S is downstream of the blade 111), so the fluid flow 1 strikes the blade 111 before it strikes the deflector 200-S, as further described in subsection 8.4.

[0370] The deflector angle of attack is shown as (i) a positive degree 259-F when the leading edge 208 of the chord line 258 of the deflector 200 is closer to the oncoming fluid flow 1 than the trailing edge 212, and (ii) a negative degree 260-A when the leading edge 208-S of the chord line 258-S of the deflector 200-S is farther from the oncoming fluid flow 1 than the trailing edge 212-S. It is important to note that the deflectors 200 and 200S can be positioned or configured at their respective angle-of-attack positions at positive or negative angles.

[0371] The deflector profile 200 has a chord line 258 at a distance 228 from the blade chord 186 into the fluid flow 1 along at least a portion of the span of the blade 111 as measured from the blade trailing edge 174 to the deflector leading edge 208, and is shown at an angle of attack 259-F of 9 degrees. The second deflector profile 200-S has a chord line 258-S at a distance 229-S downstream of the blade chord 186 along at least a portion of the span of the blade 111 as measured from the blade trailing edge 174 to the deflector leading edge 208-S and is shown at an angle of attack 260-A of -11 degrees.

[0372] Now referring to Figure 13B and still referring to Figure 13A and similar to the embodiment shown in Figure 13A , an embodiment is shown in which (i) the profile of the deflector 200, whose chord line 258 is closer to the oncoming fluid flow 1 than the profile of the blade 111 chord 186, and (ii) the second deflector profile 200-S, whose chord line 258-S is farther from the oncoming fluid flow 1 than the blade 111 chord 186, are shown.

[0373] However, compared to the deflectors 200 and 200-S shown in Figure 13A , the deflectors 200 and 200-S in Figure 13B and their corresponding chord lines 258 and 258-S are closer to the oncoming fluid flow 1 than configured in Figure 13A . In all cases in Figure 13A and Figure 13B , the respective deflector angles of attack of each deflector chord line 258 and 258-S remain constant, for example 9° and -11° respectively. In these examples, due to the distances 228-S and 229-S of the respective chord planes in Figure 13B being different from the distances 228 and 229 in Figure 13A , the respective angles of attack remain constant.

[0374] When the deflector chord lines 258 and / or 258-S advance towards the oncoming fluid flow 1, the angles of attack 259-F and 260-A can remain as shown or can also change. If the angle of attack is maintained while advancing the chord line 258 towards the oncoming fluid flow 1, then the distance 228 in Figure 13B is the same asFigure 13A the distance 228 in Figure 13B will increase compared to, and Figure 13A the distance 229-S in Figure 13B will decrease compared to the distance 229-S in Figure 13A relative to the blade chord 186. Conversely, if the vane chord is moved away from the oncoming fluid flow 1 while maintaining the angle of attack, the distance 228 in

[0375] will decrease compared to the distance 228 in

[0376] 8.2 Vertical Skew - Figure 13C

[0377] Now referring to Figure 13C , the vane leading edge 208 can be behind the blade trailing edge 174, flush with the blade trailing edge 174, or in front of the blade trailing edge 174, or displaced in a direction towards or away from the oncoming flow 1 (see Figure 13A ). The vane leading edge 208 can be skewed relative to the blade trailing edge 174 such that the distance between the blade trailing edge 174 and the vane leading edge 208 is not uniform along the vane span 223 (see Figure 9A ). The vane 200 is skewed when the chordwise spacing 229-A between the vane leading edge 208 and the blade trailing edge 174 at the tip end 218 of the vane is different from the chordwise spacing 229-E between the vane leading edge 208 and the blade trailing edge 174 at the hub end 214 of the vane.

[0378] The chordal spacing between the leading edge 208 of the deflector and the trailing edge 174 of the blade can be (i) positive when the leading edge 208 of the deflector is behind the trailing edge 174 of the blade (i.e., the leading edge 208 of the deflector lags behind the trailing edge 174 with respect to the direction of travel of the deflector / blade assembly) and (ii) negative when the leading edge 208 of the deflector is in front of the trailing edge 174 of the blade (i.e., the leading edge 208 of the deflector leads the trailing edge 174 with respect to the direction of travel of the deflector / blade assembly), where a zero distance is equal to no chordal separation between the leading edge 208 of the deflector and the trailing edge 174 of the blade (i.e., the leading edge 208 of the deflector neither leads nor lags the trailing edge 174 of the blade with respect to the direction of travel of the deflector / blade assembly). It should be noted that neither the leading edge 208 of the deflector nor the trailing edge 174 of the blade need be straight, but in one embodiment, the shape of the leading edge 208 of the deflector conforms to any curvature or non-straight portion of the trailing edge of the blade.

[0379] Depending on the position of the deflector 200 relative to the blade 111, the vertical skew can increase or decrease the global torque to adjust the output performance of the wind turbine as needed (e.g., according to the designer's choice).

[0380] 8.3 Horizontal Skew - Figure 13D

[0381] Now referring to Figure 13D , the position of the leading edge 208 of the deflector 200 relative to the trailing edge 174 of the blade 111 can be (i) closer to the oncoming fluid flow 1 than the blade 111, as shown and represented as a positive distance (horizontal spacing), or (ii) farther from the oncoming fluid flow 1 than the blade 111, and represented as a negative distance (horizontal spacing). A distance of zero between the leading edge 208 of the deflector 200 and the trailing edge 174 of the blade means there is no horizontal spacing between the leading edge 208 of the deflector and the trailing edge 174 of the blade.

[0382] The horizontal distance 228 - A between the leading edge 208 of the deflector at the deflector tip end 218 and the trailing edge 174 of the blade can be greater than, equal to, or less than the horizontal distance 228 - B between the leading edge 208 of the deflector at the deflector hub end 214 and the trailing edge 174 of the blade. Flow simulations show that the greater the horizontal distance 228 - A at the deflector tip end 218 relative to the horizontal distance 228 - B at the deflector hub end 214, the greater the increase in global torque. Flow analysis indicates that this is due to a much larger volume of fluid flowing between the leading edge 208 of the deflector and the trailing edge 174 of the blade (collectively referred to as the "edges") near their respective tip ends 151 and 218, and a much smaller volume of fluid flowing between the edges near the deflector hub end 214, which is a result of their respective circumferential velocities.

[0383] Flow simulations also show that moving the deflector 200 closer to the oncoming fluid flow 1 increases the global torque compared to that shown in Section 7. When another deflector 200 is located on the pressure side of the blade 111, facing the oncoming fluid flow 1 and advancing in the direction away from the wake of the blade 111, a greater volume of the fluid flow 1 can be used to improve the performance of the blade 111.

[0384] When the deflector 200 is located on the pressure 178 side of the blade 111, a phenomenon similar to changing the environment in which the blade 111 operates at a higher fluid flow 1 velocity (e.g., wind speed) is produced. As described above, since the increased fluid flow velocity is beneficial to the blade 111, this phenomenon increases when the deflector 200 is moved closer to the oncoming fluid flow 1.

[0385] 8.4 - Suction - side deflector position - Figure 13E

[0386] Now referring Figure 13E , the flow simulations show that when the deflector 200 - S is located on the suction side 182 of the blade 111, a global torque improvement can be obtained when the recess 230 - S and the protrusion 238 - S are smaller than when the deflector 200 is located on the pressure side 178 of the blade 111. This is because, when configured as shown on the suction side 182 of the blade 111 and when used in combination with a deflector 200 (configuration not shown) located on the pressure side of the blade 111, the deflector 200 acts like a flow corrector rather than a deflector, thus reducing the turbulence and suction near the beneficial area 16 at the trailing edge of the suction surface 182 (see Figure 2G ).

[0387] 9. Alternative embodiments

[0388] The alternative embodiments described herein can be used for any (i) fluid type, i.e., air and water, and (ii) combination with any deflector / blade assembly or its alternative embodiments, i.e., a deflector with a curved tip (see subsection 9.3), and the fluid wall (see subsection 9.5) can be combined, regardless of the drawings or text describing such alternative embodiments.

[0389] 9.1 Partial - span deflector - Figures 14A - 14E

[0390] The partial - span deflector 200 - A can embody all the features and properties of the deflector 200, including but not limited to the connector tube 270 as described in Section 6 and shown in Figure 9K , Figure 9L , Figure 9M , Figure 9N and the leading - edge and trailing - edge features.

[0391] The partial-span splitter 200-A can be retrofitted anywhere along the span of an existing turbine blade, according to the designer's choice, e.g., to improve turbine performance when the turbine is operating at its rated capacity. Flow simulations and physical tests indicate that the partial-span splitter increases the global torque per square area of the pressure and suction surfaces of the splitter 200-A, similar to but less than the splitter 200 that substantially extends the full span of the blade. Flow simulations also indicate that a partial-span splitter with a longer span generates a greater global torque per square area than a partial-span splitter with a shorter span. Thus, flow simulations indicate that a longer splitter that is twice the area of a shorter splitter will more than double the global torque compared to the shorter splitter.

[0392] Now referring to Figure 14A , the partial-span splitter 200-A is constructed on the pressure side 178 of the blade 111, approximately midway between the blade tip 151 and the root end 158.

[0393] Now referring to Figure 14B , and still referring to Figure 14A , the partial-span splitter 200-A is fixedly linked to the blade 111 via a connector assembly 261-A, which includes an externally blade-end flange 272-A that is fixedly linked. The connector assembly 261-A implements the same aerodynamic characteristics as the connector assembly 261 described in Section 6 and shown in Figure 9K , Figure 9L , Figure 9M , Figure 9N , including but not limited to, thereby its (i) implementing two sets of leading and trailing edges; as described above, one set of leading and trailing edges is affected by and minimized the drag of the oncoming fluid flow, and the second set of leading and trailing edges is affected by and minimized the drag (apparent velocity) of the fluid flow, and (ii) having an elliptical and / or oval profile that is aligned and oriented with the rotational flow.

[0394] Now referring to Figure 14C and Figure 14D , in one embodiment, the connector assembly 261-A includes a tube 270-A, the tube 270-A having a fixedly linked splitter-end flange 271-A and a fixedly linked blade-end (pressure side) flange 272-A and one or more studs 291-A, 291-B, 291-C, and 291-D (collectively referred to as "flange studs") that project from and are fixedly linked to the blade-end flange 272-A.

[0395] Now referring to Figure 14D , and still referring to Figure 14C, the connector 261 - A includes a suction - side flange 293 - A and tubes 292 - A, 292 - B, 292 - C, and 292 - D (collectively referred to as "flange tubes") that project from and are fixedly linked to the suction - side flange 293 - A. The flange studs 291 - A, 291 - B, 291 - C, 291 - D (i) penetrate the pressure surface 178 of the vane 111, (ii) pass through the flange tubes 292 - A, 292 - B, 292 - C, 292 - D (which penetrate the suction surface 182 of the vane 111) and the suction - side flange 293 - A, and (iii) are fixed with fasteners 295 (e.g., nuts on the threaded ends of the flange studs 291 - A, 291 - B, 291 - C, 291 - D that project from the suction - side flange 293 - A) or other suitable means (e.g., welding, etc.) for fixing the ends of the flange studs 291 - A, 291 - B, 291 - C, 291 - D relative to the suction - side flange 293 - A.

[0396] Now refer to Figure 14E , while still referring to Figure 14C and Figure 14D , the geometries (profiles) of the pressure - side vane - end flange 272 - A and the suction - side flange 293 - A conform to the respective vane pressure surface 178 and suction surface 182 with which they mate (see Figure 2B ). The length of each flange stud and the corresponding length of the flange tube can be different to accommodate variations in the spacing between the vane pressure surface and the suction surface that respectively mate with the flanges 272 - A and 293 - A, i.e., the flanges can be tapered and / or twisted.

[0397] The lengths of the flange tubes 292 - A, 292 - B, 292 - C, 292 - D can be dimensioned to be smaller than the spacing between the vane pressure surface 178 and the suction surface 182 (see Figure 2C ) to achieve a compression fit between the flanges 272 - A and 293 - A and the vane 111 while preventing the fasteners 295 from compressing the vane 111 beyond the designer's choice.

[0398] Additionally, the mechanical attachment of the pressure - side vane - end flange 272 - A and the suction - side flange 293 - A can be chemically bonded or otherwise adhered to the exterior of the vane 111, and the mechanical attachment of the flange tubes can be chemically bonded or otherwise adhered to the structure through which the flange tubes 292 - A, 292 - B, 292 - C, 292 - D pass inside the vane 111.

[0399] The connector assembly 261 - A conforms to the twist of the deflector / vane assembly and the undulations of the deflector 200 - A, so the twist and / or length or angle of the connector assembly 261 - A can vary over the deflector span 223 (see [[ ).

[0400] The connector tube 270-A can embody all the benefits and features of the leading and trailing edges of the connector tube 270 as described in Section 6, including but not limited to two sets of leading and trailing edges. When the vane / deflector assembly is stationary, one set of leading and trailing edges works against the oncoming wind flow, and when the vane / deflector assembly rotates, the other set of leading and trailing edges works with the rotational flow.

[0401] 9.2 Non-uniform thickness deflector - ​

[0402] Now referring to ​ and ​ Details A - C, an embodiment of the deflector 200-B includes a pressure surface 204-B, which can substantially mirror the pressure surface 204 of the deflector 200 having a similar overall shape, size, and geometry (see Figure 9A ), but the deflector 200-B does not have a uniform thickness. The deflector 200-B differs from the deflector 200 in that it has a more traditional airfoil shape than the deflector 200, whereby the deflector 200-B is thicker between the pressure surface 204-B and the suction surface 206-B near the leading edge 208-B and thinner between the pressure surface 204-B and the suction surface 206-B near the trailing edge 212-B ("suction side airfoil"). The deflector 200-B has an airfoil shape profile that creates a pressure differential between the upstream (pressure) surface 204-B and the downstream (suction) surface 206-B due to the relative fluid flow on the upstream and downstream surfaces. The pressure surface 204-B of the deflector 200-B can have recesses 230 and / or protrusions 238 that are similar or substantially the same as the recesses 230 and / or protrusions 238 on the pressure surface 204 of the uniform thickness deflector 200 (see Figure 9A ).

[0403] The non-uniform thickness on the suction side can be used to increase the global torque by creating an upstream / downstream pressure differential (lift) that depends on (i) the relative horizontal and vertical positions of the deflector 200-B with respect to the blade 111 to which it is fixedly linked or operably (adjustably) coupled, (ii) the shape and size of the deflector 200-B, (iii) the angle of attack of the deflector 200-B, and (iv) the depth of the protrusions and recesses (see Sections 3, 5, and Subsection 8.1).

[0404] The thickness between the pressure surface 204-B and the suction surface 206-B of the deflector 200-B can vary from the tip end 218-B to the hub end 214-B of the deflector 200-B at any point between the leading edge 208-B and the trailing edge 212-B.

[0405] The flow deflector 200 - B can be used on the pressure side 178 or the suction side 182 of the blade 111 in place of the flow deflector 200 (see respectively Figure 2A and Figure 2B ). However, due to the thickened profile of the flow deflector 200 - B, its suction side 206 - B has different flow characteristics from those of the flow deflector 200.

[0406] The flow deflector 200 - B can have an internal structure similar to that of the blade 111 (see Section 1 and Figure 2C ).

[0407] 9.3 Curved tip - Figure 16A

[0408] Now referring to Figure 16A and Figure 16B , an embodiment of the flow deflector 200 - C includes a curved section 219 along a portion of the trailing edge 212, which increases the global torque by reducing the drag on the flow deflector 200 - C. The end trailing - edge corner at the tip 218 of the trapezoidal flow deflector (see Figure 9A ) generates a negative torque. By removing this corner in the area of the flow deflector tip 218, this negative torque can be reduced, resulting in a net gain in global torque even if the area of the flow deflector is reduced. By deviating the shape of the trailing edge 212 such that the flow deflector chord is shorter at the flow deflector tip 218 than it would be if the trailing - edge shape were not deviated, the corner is removed or at least its size is reduced. For example, the trailing - edge corner can be removed by providing a curved trailing - edge section 219 that starts at or near the leading edge 208 of the flow deflector at the flow deflector tip end 218 and ends at a point 220 that can be up to one - third of the distance between the flow deflector tip end 218 and the hub end 214.

[0409] The curved section 219 can be optimized to increase the global torque by changing the curvature and length of the curved section 219. Additionally, a straight trailing - edge section can be provided instead of the curved trailing - edge section 219, which starts at or near the leading edge 208 of the flow deflector at the flow deflector tip end 218 and ends at a point 220.

[0410] 9.4 Arcuate tip - Figure 17A

[0411] Now referring to Figure 17A, An embodiment of the spoiler 200-D includes an arcuate tip section 231-D that increases global torque. The arcuate tip section 231-D is provided by deviating the shape of the trailing edge 212-D such that the chord of the spoiler is longer at the spoiler tip end 218-D than it would be if the trailing edge shape were not deviated. In this subsection, for ease of readability and understanding, the spoiler 200-D has been superimposed on the spoiler 200 of the same size, except for the arcuate tip section 231-D, with the non-deviated trailing edge 212 shown in dashed lines. Thus, in this subsection, any part number without a hyphen and letter at the end refers to the spoiler 200 for comparison. Additionally, for illustrative purposes, the end and cross-sectional detail views (respectively Figure 17B and Figure 17C ) have wide cross-hatching to depict the extended arcuate region 231-D and narrow cross-hatching to depict the portions of the spoiler 200 that have been included to aid in understanding the extended arcuate tip region. The change in cross-hatching direction has no significance to the construction of the spoiler 200-D as the spoiler 200-D can include a single integral structure and is not intended to necessarily indicate that the spoiler 200-D is formed of multiple components and / or different materials in the region of section 231-D.

[0412] The arcuate section 231-D extends from the trailing edge 212 of the spoiler 200 (see also Figure 9A ), and has an arcuate (or curved) trailing edge 212-D that defines a gradually increasing chord from the intersection point 234-D to the tip end 218-D between the leading edge 208 and the arcuate trailing edge 212-D. The arcuate tip section 231-D includes a chord extension 232-D from the trailing edge 212 to the extended trailing edge 212-D, and a length 233-D that extends from the spoiler tip end 218-D to the intersection point 234-D where the arcuate section trailing edge 212-D intersects the trailing edge 212. The intersection point 234-D can be located at any point along the span of the spoiler 200-D up to the hub end 214-D.

[0413] Now referring to Figure 17B , and still referring to Figure 17A , the arcuate tip section 231-D includes a convex portion 235-D on the pressure side 204-D that extends between the trailing edge 212-D and the extension of the trailing edge 212 to 212-D (see the dashed lines in Figure 17A ).

[0414] Now referring to Figure 17C , and still referring to Figure 17B and Figure 17A , starting from the spoiler tip end 218-D, the arcuate tip section 231-D substantially fills the area defined by the extension of the trailing edge 212 ( Figure 17AThe space outlined by the dashed line (in ), a portion of the suction surface 206 of the extension near the trailing edge 212, the arcuate tip suction surface 206-D, the arcuate tip pressure surface 204-D, and the arcuate section trailing edge 212-D is depicted with wide cross-hatching. The width and curvature of the filled space can vary across the span of the arcuate section 231-D, and thus the chord can vary accordingly. The arcuate tip section 231-D is depicted as a superimposed extension of the deflector 200, which is shown with narrow cross-hatching.

[0415] In the illustrated embodiment, the cross-sectional area (the thickness between the pressure surface 204-D and the suction surface 206-D) of the arcuate tip section 231-D decreases from the deflector tip 218-D to the intersection point 234-D and follows the deflector twist between the tip end 218-D and the hub end 214-D.

[0416] The curvature, length, and cross-sectional area of the curved section 231-D can be varied according to the designer's choice to increase the global torque.

[0417] 9.5 Fluid wall- Figures 18A - 18B

[0418] Now referring to Figure 18A and Figure 18B , an embodiment of the deflector 200-E includes one or more walls 600 protruding from one or both surfaces of the deflector 200-E (shown protruding from the pressure surface 204 in Figure 18A , Figure 18B ). Each wall 600 can extend from the leading edge 208 to the trailing edge 212 or any portion thereof and can follow a corresponding rotational travel path 275 around the rotor axis of rotation 123 (see Figure 1A ), or be straight or curved along an arc other than the rotational travel path 275. The deflector 200-E can also include transverse walls 620 extending along or near the trailing edge 212 from one or more walls 600. The walls 600 and the transverse walls 620 are fixedly linked to the deflector 200-E and extend from the pressure surface 204 towards the oncoming fluid flow or from the suction surface 206 (see details A, B, and C in Figure 9A , showing the suction surface 206) towards the downwind flow. The walls 600, 620 can be perpendicular or otherwise oriented relative to the pressure surface 204 and / or the suction surface 206.

[0419] The walls 600 reduce the spillage of the fluid moving from the deflector tip end 218 towards the hub end 214, causing the center of mass (center of pressure) to move towards the tip end 218 of the blade 111, thereby increasing the global torque.

[0420] The wall 600 may have a uniform or non-uniform height from the front end to the back end of the wall, and has a rotational flow leading edge 601, an oncoming fluid flow leading edge 602, and a rotational flow trailing edge 603 (collectively referred to as "the wall 600 edges"). The wall 600 edges may be straight, tapered, beveled, or curved to reduce drag or otherwise improve performance characteristics, including but not limited to increasing global torque.

[0421] The lateral wall 620 reduces fluid spillage along the trailing edge 212, thereby increasing global torque. The height of the lateral wall 620 may be the same as or different from the height of the wall 600. Although the configuration of the lateral wall 620 may result in drag on the rotating blade / vane assembly, the flow simulation results show that the performance improvement of the lateral wall 620 is greater than the drag it causes.

[0422] The lateral wall 620 edges may be straight, tapered, beveled, or curved to reduce drag or otherwise improve performance characteristics.

[0423] Two or more walls 600 having different lengths and heights may be configured anywhere along the vane span 223 (see Figure 9A ) on the pressure side 204 of the vane 200-E.

[0424] One or more lateral walls 620 having different lengths and heights may be configured near the trailing edge 212 along the vane span 223 (see Figure 9A ).

[0425] 9.6 Multi-component vane and connector assembly - Figure 19A and Figure 19B

[0426] The vane and / or connector assembly may be provided in a multi-component arrangement. The multi-component vane 201 (see Figure 19A ) and the multi-component connector 261-B (see Figure 19B ) achieve the following combination, which allows (i) the installation or replacement of the entire vane by simply removing a pin or other similar fastener from the multi-component connector 261-B, as further described below, (ii) the segmented installation of the multi-component vane 201 (see Figure 19A ), rather than an integral vane, thereby reducing the time, cost, and difficulty of transporting the blade / vane assembly, and (iii) in the case where a part of the vane and / or connector assembly needs to be repaired, simply replacing the damaged vane section, such as section 201-B (see Figure 19A ). This feature is particularly valuable because the airfoil section 164 designed to affect the blade 111 (see Figure 2A) All or most of the connectors for the deflector can be fixedly linked to the internal structure within the blade during its manufacture. Thus, without this feature, the repair of a damaged deflector would be more complex and costly. It is important to note that Figure 19A The illustration in

[0427] is of the suction side. Thus, its cropped cross-sectional view appears inverted. Figure 19A As shown in Figure 9A , the multi-piece deflector 201 includes a plurality of adjacent segments 201-A - 201-E. In the example shown, each of the segments 201-A, 201-B, 201-C, 201-D, and 201-E is associated with and attached to at least one connector assembly 261-B, although this is not required. When assembled, the geometry of a particular multi-piece deflector 201 can be substantially the same in all respects as the geometry of the same design of a single-piece deflector 200 (e.g., as shown in Figure 9A ).

[0428] The adjacent segments of the multi-piece deflector 201 (e.g., segments 201-A and 201-B, segments 201-B and 201-C, segments 201-C and 201-D, and segments 201-D and segment 201-E) can be connected to each other by connectors that include parallel top and bottom plates connected to each other, and the adjacent ends of the adjacent segments are sandwiched between the top and bottom plates and held together. For example, as shown in detail B of Figure 19A , the connector for connecting segments 201-B and 201-C includes a top plate 202-C and a bottom plate 202-D, and the ends of segments 201-B and 201-C are adjacent to each other and sandwiched between bottom plate 202-D and top plate 202-C. Preferably, a protrusion is provided on the top and bottom surfaces of the adjacent ends of the adjacent segments such that the bottom and top plates are substantially flush with the pressure surface 204 and the suction surface 206 of the deflector 201.

[0429] Figure 19A The bottom plates 202-B of the connectors connecting adjacent segments 201-A and 201-B, the bottom plate 202-D of the connector connecting adjacent segments 201-B and 201-C, the bottom plate 202-F of the connector connecting adjacent segments 201-C and 201-D, and the bottom plate 202-H of the connector connecting adjacent segments 201-D and 201-E are shown. As shown in Figure 19A and Figure 19AAs shown in Detail A, the connector can be oriented at an angle relative to a line (e.g., a cord line) extending between the leading and trailing edges of the deflector 201-E. Benefits of the angled connection include (i) self-aligning the section joint with the positive stop, thus allowing for faster and more precise installation and assembly compared to non-angled joints, and (ii) making the section joint more robust due to the increased surface area obtained from the increased length of each joint.

[0430] In addition, as Figure 19A and Figure 19A shown in Detail A, a plurality of fasteners connect the top plate and the bottom plate, thereby holding adjacent sections sandwiched between the plates together. For example, as Figure 19A shown in Detail B, mechanical fasteners 202-P (e.g., screws, bolts, rivets, etc.) connect the top plate 202-C to the bottom plate 202-D. One set of fasteners 202-P that connect the top plate 202-C to the bottom plate 202-D extends through the end of section 201-B, and another set of fasteners 202-P that connect the top plate 202-C to the bottom plate 202-D extends through the end of section 201-C. Adhesives can be used to fix the top plate 202-C and the bottom plate 202-D to adjacent deflector sections (with or without the use of fasteners 202-P), although the use of adhesives may mean that the top plate 202-C and the bottom plate 202-D cannot be removed from the deflector by simply removing the fasteners 202-P to replace a damaged deflector section (as described above).

[0431] 9.6.1 Multi-Part Connector

[0432] Now referring to Figure 19B and still referring to Figure 19A , in some embodiments, the connector tube of the connector assembly 261 can be separable into two or more parts. For example, as Figure 19B shown, the multi-part connector assembly 261-B can include a first (or upper) tube section 270-A and a second (or lower) tube section 270-B that can be connected to the first tube section 270-A. In one example, as Figure 19BAs shown in detail A and B, the first tube section 270-A and the second tube section 270-B can be connected by a joint that includes a tongue 270-C received within a mating groove 270-D. The tongue 270-C is retained within the groove 270-D by a retaining pin 270-G that extends through a hole 270-F formed in an end of the lower section 270-B on opposite sides of the groove 270-D and is aligned with a hole 270-E formed in the tongue 270-C. In the illustrated embodiment, the tongue 270-C is formed on the first tube section 270-A and the groove 270-D is formed on the second tube section 270-B, but the components can be reversed such that the tongue 270-C is formed on the second tube section 270-B and the groove 270-D is formed on the first tube section 270-A.

[0433] The multi-component deflector can be delivered to the installation site in an unassembled state and the sections 201-A - 201-E can be attached to one another by placing adjacent sections with their ends adjacent to one another and placing the top plate 202-C and bottom plate 202-D of the associated connector assembly above and below the adjacent ends. Holes that are aligned with fastener holes formed in the top plate 202-C and bottom plate 202-D can be pre-formed in the adjacent deflector sections or can be formed in situ (e.g., drilled), and fasteners 202-P are inserted through the aligned holes. The first section 270-A of the connector assembly 261-B will be attached to each of at least some of the deflector sections and the mating second section 270-B of each connector assembly 261-B will be attached to the vane to which the deflector 201 will be attached. The first section 270-A is connected to the second section, for example, by the tongue 270-C, groove 270-D, and retaining pin 270-G described above.

[0434] To replace one or more sections of the multi-component deflector 201, the fasteners 202-P that retain the connector assembly of the section to be replaced are removed and, if any of the sections to be replaced are connected to the connector assembly 261-B, the retaining pin 270-G is removed to allow the upper section 270-A to be separated from the lower section 270-B. The replacement section is then placed in position with its ends disposed between the top plate 202-C and bottom plate 202-D of the connector assembly and adjacent to the ends of the adjacent deflector sections, and the tongue 270-C is placed into the groove 270-D. The fasteners 202-P are placed through the ends of the replacement section into the top plate 202-C and bottom plate 202-D and the retaining pin 270-G is inserted into the aligned holes 270-F and 270-E of the tube sections 270-A and 270-B. The retaining pin is one method of connecting the first section 270-A of the connector assembly and the second section 270-B of the connector assembly. However, one of ordinary skill in the art can use other methods, including U-bolt pins, brake U-bolt pins, safety pins, nuts, and bolts.

[0435] 9.7 Variable Angle Connector Assembly - Figures 20A - 20I

[0436] Now referring to Figure 20A , an airfoil embodiment includes a power variable angle connector assembly (VAC assembly) capable of changing the angle of attack of the airfoil. This embodiment is capable of (i) controlling and / or improving the performance of the airfoil / vane assembly over the range of fluid velocities at which the assembly operates, (ii) causing the vanes that benefit from the airfoil to begin rotating and converting kinetic energy even earlier than flow simulations and physical tests indicate they would otherwise achieve, and (iii) serving as a braking device.

[0437] Still referring to Figure 20A , in one embodiment, the VAC assembly 261 - E visible on the suction side 206 of the airfoil 200 and the suction side 182 of the vane 111 is fixedly linked within the vane 111 and fixedly linked to the airfoil 200. The connector assembly 261 - E conforms to the twist of the airfoil / vane assembly and the camber of the airfoil 200, such that the twist and / or length or angle of the connector assembly 261 - E can vary over the airfoil span 223 (see Figure 9A ).

[0438] The VAC assembly 261 - E connects the airfoil 200 to the vane 111 and is configured to enable and effect a powered adjustment of the airfoil angle of attack, as will be described. Such powered adjustment can be automated and computer - controlled.

[0439] As described in subsection 8.1, changing the angle of attack of the airfoil 200 is a variable factor that affects the impact of the airfoil on the vane 111 and thus affects the overall performance of the airfoil / vane assembly and the rotor.

[0440] 9.7.1 Optimal Positions - Figure 20B

[0441] Now referring to Figure 20B , while still referring to Figure 20A , the airfoil chord line 258 is depicted in five positions relative to the rotor plane of rotation 104, denoted as the 10° angular ranges 263 - A, 263 - B, 263 - C, and 263 - D. For the sake of clarity of the illustration in Figure 20B , the profile of the airfoil 200 is not shown. The trailing edge of the airfoil will be in the region of 212 - T, which is near the top of Figure 20B , and the leading edge of the airfoil will be in the region of 208 - L, which is near the lower part of Figure 20B . In this embodiment, the airfoil 200 is hinged about the point 262 (also see Figure 20C), and has performance characteristics associated with the deflector angle of attack ("AoA"), and is positioned as follows:

[0442] AoA Range or Position Performance Characteristics 263-A Generate Drag; Act as a Brake 263-B Improve Performance 263-C Improve Performance 263-D Generate Drag, Act as a Brake 264 Fully Extended Position; Act as a Brake 26. Optimal Position to Start Rotation 266 Optimal Position at 13 m / s 267 Fully Retracted Position; Act as a Brake

[0443] In addition to the blade performance improvements detailed in Section 7, additional blade performance improvements can be achieved by varying the deflector angle of attack across the entire speed range. For example, in physical tests, at wind speeds insufficient to cause a blade without a deflector to start rotating, a blade benefiting from a deflector starts rotating earlier at the same wind speed, e.g., starting to rotate at wind speeds less than 1.12 m / s, compared to a blade without a deflector that starts rotating at a wind speed approaching 2.25 m / s, and a blade benefiting from a deflector outperforms a blade not benefiting from a deflector across the entire speed range. However, if the deflector angle of attack is moved to position 265 under conditions where the oncoming fluid flow 1 velocity is 0.0 - 0.9 m / s, the rotor will start rotating at 0.67 m / s, and by adjusting the deflector angle of attack from position 265 to position 266 as the oncoming fluid flow 1 velocity increases, additional global torque will be obtained since the deflector 200 has an optimal angle of attack across the entire blade 111 speed range.

[0444] 9.7.2 Overview of Actuation Details - Figure 20C and Figure 20D

[0445] Now referring to Figure 20C and Figure 20D while still referring to Figure 20B , the cutaway section reveals the actuating components and the deflector to VAC connector connection. Figure 20C The deflector is shown in its fully extended position 264 (representing one end of the deflector angle of attack range), and Figure 20D the deflector is shown in its fully retracted position 267 (representing the opposite end of the deflector angle of attack range). It should be noted that the term "fully extended" refers to the position of the deflector relative to the rotation plane 104 (see Figure 20B ). Thus, in the illustrated embodiment, when the deflector 200 is in its fully extended position, the flexible shaft assembly 550 is in its fully retracted position, and likewise, when the deflector 200 is in its fully retracted position, the flexible shaft assembly 550 is in its fully extended position.

[0446] The connector assembly 261-E includes a pivot spar 270-H that has a flange 272-H at one end, and the flange 272-H is connected (e.g., by mechanical fasteners, etc.) to a U-shaped web 116 within the vane 111. The pivot spar 270-H projects through an opening in the vane 111 at or near the trailing edge 174 of the vane and extends to a position spaced behind the trailing edge 174 of the vane. The deflector end flange 271-H is attached to the deflector 200 and includes a pivot connection 262 at which the end of the spar 270-H is pivotally connected to the flange 271-H. Details of this connection are given in Subsection 9.7.4.

[0447] In the illustrated embodiment, the spar 270-H is connected to the flange 271-H (and thus to the deflector 200) closer to the trailing edge 212 of the deflector than to the leading edge 208 of the deflector. The flexible shaft assembly 550 is connected to the flange 271-H closer to the leading edge 208 of the deflector than to the trailing edge 212 of the deflector and is configured such that the deflector 200 pivots about the end of the pivot spar 270-H at the pivot connection 262, thereby selectively changing the angle of attack of the deflector 200.

[0448] In the illustrated embodiment, the motor 650 rotates the shaft 652, which drives the right-angle drive 655, which rotates the drive screw 656, thereby causing the collar 670 to move axially along the length of the drive screw 656, which causes the corresponding axial movement of the convex guide tube 680 (see also Subsection 9.7.6), which causes the flexible shaft assembly 550 to extend and retract to change the angle of attack of the deflector 200. In this embodiment, the motor 650 is located at the position closest to the hub end of the vane 111. However, the motor 650 can alternatively be located at any position along the vane span 154 (see Figure 2A ) or within the hub 121 (see Figure 1A ).

[0449] The 40-degree range of motion of the VAC connector (see Figure 20B ) can be extended in a variety of ways, including by (i) moving the pivot point 262 closer to the pivot point 563, or (ii) extending the screw 656 and positioning the motor 650, shaft 652, right-angle drive 655, shaft 660, and balance pieces of the associated shafts and right-angle drives (see Figure 20E ) below the support 119 and increasing the curvature of the spar 270-H, thereby increasing the travel distance between the trailing edge 208 and the pivot spar 270-H, or (iii) swapping the positions of the pivot points 262 and 563, or (iv) any combination of methods (i)-(iii).

[0450] The flexible shaft assembly 550 includes a flexible shaft 566 that is pivotally connected at one end to a flange 271-H and anchored at the opposite end within a vane 111. The flexible shaft 566 extends through a flexible shaft guide tube 565 which, in the illustrated embodiment, is part of a pivot spar 270-H. The end of the flexible shaft 566 anchored within the vane 111 is coupled to a drive screw assembly 665 which, as will be described, is configured (see Figure 20H ) to effect powered (e.g., motorized) axial movement of the flexible shaft 566 to vary the amount by which the flexible shaft 566 extends from the vane 111, thereby causing the deflector 200 to which the flexible shaft 566 is attached to pivot about a pivot connection 262 and change the angle of attack of the deflector 200.

[0451] 9.7.3 Main Drivetrain Components - Figure 20E

[0452] Now referring to Figure 20E and still referring to Figure 20C , if the deflector / vane assembly includes a plurality of VAC connector assemblies 261-E, the right angle drive 655 can also rotate a shaft 660 that is connected to a subsequent right angle drive for an adjacent VAC connector assembly 261-E such that a single motor 650 can simultaneously actuate all of the VAC connector assemblies 261-E.

[0453] The illustrated right angle drive and associated drive shaft configuration can be repeated along the length of the deflector span 223 (see Figure 9A ) and thereafter drive each subsequent VAC connector assembly 261-E. In this embodiment, the motor 650 drives a shaft 652 which drives a right angle drive 655, a screw 656, and a shaft 652-A which drives a right angle drive 655-A, a screw 656-A and a shaft 652-B which drives a right angle drive 655-B, a screw 656-B and a shaft 652-C which drives a right angle drive 655-C, a screw 656-C and a shaft 652-D which drives a right angle drive 655-D and a screw 656-D.

[0454] Other embodiments of the VAC connector can include one or more motors similar to the motor 650 located anywhere along the vane span 154 (see Figure 2A ), e.g., near the middle of the vane span 154, or within a hub 121 (see Figure 1A ) not shown. Similarly, the computer that controls the motor 650 can be located anywhere within the turbine 100 (see Figure 1A ).

[0455] 9.7.4 VAC Pivot Point Details - Figure 20F

[0456] Reference Figure 20F , the pivot spar 270-H pivots about a pivot axis 262-A at a pivot point 262. In one example, the pivot point 262 (see Figure 20C and Figure 20D ) that is collinear with the pivot axis 262-A may include spaced-apart spar brackets 501 protruding from a flange 271-H. A bushing 504 is press-fitted into a hole 503 formed in an end of the spar 270-H, and the end of the spar 270-H is received between the spar brackets 501, wherein the bushing 504 and the hole 503 are aligned with holes 502 formed in the spar brackets 501. A bushing 505 (which may be a self-lubricating bushing) is inserted through one of the holes 502 into one end of the bushing 504, and a top hat bushing 506 is inserted through the opposite hole 502 into the opposite end of the bushing 504 and preferably contacts the bushing 505 within the bushing 504. A bolt 507 is inserted through the holes 502 and the bushings 506 and 505 and is fixed at its ends by a nut 508. The bolt and nut are one method of attachment that may be used at pivot points 262 and 563 (see Figure 20C and Figure 20D ). However, one of ordinary skill in the art may use other methods, including U-bolt pins, brake U-bolt pins, and safety pins.

[0457] 9.7.5 Flexible Shaft Pivot Points and Shaft Details - Figures 20F - 20G

[0458] Now refer to Figure 20G , while still referring to Figure 20F , in one example, a flexible shaft 566 is pivotally attached to a flange 271-H at a pivot point 563 (see Figure 20C ) to pivot about a pivot axis 563-A at a pivot connector that is spaced from a pivot connector 262 (see Figure 20C ) along the chordwise direction of the deflector toward the leading edge 208 of the deflector, thereby connecting the spar 270-H to the deflector at a pivot point 262 (see Figure 20C ). The pivot point 563 (see Figure 20C) may include spaced flexible shaft brackets 561 projecting from the flange 271-H. A bushing 570 is press-fitted into a hole 560-A formed through a connector cap 560 provided at the end of the flexible shaft 566, and the connector 560 is received between the flexible shaft brackets 561, wherein the bushing 570 and the hole 560-A are aligned with holes 562 formed in the flexible shaft brackets 561. A first bushing 572 (which may be a self-lubricating bushing) is inserted through one hole 562 into one end of the bushing 570, and a second bushing 572-A is inserted through the opposite hole 562 into the opposite end of the bushing 570 and preferably contacts the first bushing 572 within the bushing 570. A bolt 575 is inserted through the holes 562 and the bushings 572 and 572-A and is fixed at the end by a nut 578.

[0459] One or more seals or other devices may be provided to prevent moisture or debris from penetrating along the flexible shaft 566 into the flexible shaft guide tube 565. As Figure 20F and Figure 20G shown, an O-ring 542 may be provided around the flexible shaft 566 and positioned in the O-ring seat 544. The O-ring 542 is a design to prevent fluid from entering the flexible shaft guide tube 565. However, a person of ordinary skill in the art may use various types and numbers of seals for this purpose.

[0460] 9.7.6 Guide Tube Assembly Details - Figures 20H - 20I

[0461] Referring Figure 20H , the end of the flexible shaft assembly 550 is mounted within the vane 111 (see Figure 20C and Figure 20D ) for limited axial movement within the guide tube assembly 690. The guide tube assembly 690 including the guide tube housing 692 may be fixed between the webs 116 and 117 by bolts 287 extending through the flange 271-H, the web 116, and through holes 688 formed in the housing 692, the web 117, and the lower flange 281-A. The bolts 287 may be fixed by nuts (not shown), or the lower flange 281-A may be threaded.

[0462] The flexible shaft 566 is disposed within a guide tube hole 685 (see Figure 20I ) in the guide tube housing 692. A diameter of a stop 555 fixedly attached at the end of the flexible shaft 566 is slightly smaller than a diameter of the hole 685 such that the stop 555 and the flexible shaft 566 can axially move within the hole 685, but is larger than diameters of holes formed in the web 116 and the flange 272-H (the diameters of which are slightly larger than the diameter of the flexible shaft 566). The stop 555 contacts the web 116 to prevent the flexible shaft 566 from being pulled out of the guide tube housing 692 together with a stop 681 described below.

[0463] The flexible shaft actuator is coupled to a flexible shaft 566 to effect selective powered (e.g., motorized) axial movement of the flexible shaft 566 within a guide hole 685. In the illustrated embodiment, the flexible shaft actuator includes a drive screw assembly 665. The drive screw assembly 665 includes a convex guide tube 680 disposed for axial movement within a guide tube bore 685.

[0464] The drive assembly 665 further includes a drive screw 656 extending into an axial blind hole formed in the convex guide tube 680. A collar 670 having a ball screw bearing 671 is operatively coupled to the drive screw 656 such that rotation of the drive screw 656 causes a corresponding axial movement of the collar 670 along the length of the drive screw 656. The collar 670 abuts and may be connected to a stop 681 of the convex guide tube 680 such that axial movement of the collar 670 along the drive screw 656 causes a corresponding axial movement of the convex guide tube 680. An end of the convex guide tube 680 opposite the stop 681 abuts and may be connected to a stop 555 of the flexible shaft 566 such that axial movement of the convex guide tube 680 causes a corresponding axial movement of the flexible shaft 566 within the guide tube bore 685. When the flexible shaft 550 is fully extended, the stop 681 contacts the flange 281-A, thereby restricting its travel with the stop 555 as described above. The guide tube housing 692 may be longitudinally separated and fastened together (not shown) to facilitate assembly of the flexible shaft assembly 550 and the drive screw assembly 665.

[0465] Now referring Figure 20I , keys 682, 683 received within keyways 682-A, 683-A respectively prevent rotation of the convex guide tube 680 within the guide tube bore 685. A stop 681 at the lower end of the convex guide tube 680 contacts the bottom of a concave guide tube 693 disposed within the housing 692 to limit travel of the convex guide tube 680 within the bore 685 and thus limit travel of the flexible shaft assembly 550 (see Figure 20G ). The convex guide tube 680 and the concave guide tube 693 may be composed of or include materials selected by the designer, including low friction high strength metals and plastics such as oil impregnated sintered bronze and acetal homopolymer such as

[0466] 10. Blades and Deflectors - Simulated Geometries - Figures 21A - 21D

[0467] The following subsections include the CAD dimensional data of the deflector 111 and the position of the deflector 200 relative to the blade 111 when it undergoes the flow simulation as described in Section 7.

[0468] 10.1 Deflector Dimension Data -Figures 21A - 21D

[0469] Now referring to Figure 21A , a side profile schematic diagram of an embodiment of the deflector 200 is shown, which shows 11 reference points 900 - 910 along the chord, starting from point 900 at the leading edge 208 and point 910 at the trailing edge 212.

[0470] Now referring to Figure 21B , while still referring to Figure 21A , this table provides the profile dimension data of the deflector, which is modeled for flow analysis in the X and Y coordinates of profiles A, B, C, D, and E (where the leading edge 208 is the origin (0,0) of the coordinate system).

[0471] Now referring to Figure 21C , while still referring to Figure 21A and Figure 21B , the front view of the deflector 200 shows the intersection points from which the profile measurements in the table in Figure 21B are obtained. Figure 21C The cross-sections A - A, B - B, C - C, D - D, and E - E in Figure 21B correspond to the table columns A, B, C, D, and E in

[0472] Figure 21D A table showing the offset dimensions in the Z (spanwise) direction from the tip of the blade (corresponding to profile A of cross-section A - A in Figure 21C to profiles B, C, D, and E corresponding to cross-sections B - B, C - C, D - D, and E - E in Figure 21C respectively).

[0473] Now referring to Figures 21A - 21D , the geometric dimension data of the deflector 200 can be obtained at each of the reference points 900 - 910 in profiles A to E corresponding to cross-sections A - A, B - B, C - C, D - D, and E - E in Figure 21C respectively. For example, according to Figure 21A and Figure 21B and 21D , the (X, Y, Z) coordinates (dimension data) of reference point 901 on profile B with respect to the leading edge 208 at the tip end of the deflector 200 (i.e., profile A) are (0.142 m, 0.008 m, 9.113 m).

[0474] 10.2 Position of the deflector relative to the blade - Figures 22A - 22B

[0475] Now referring to Figure 22A, the blade 111 and the deflector 200 (whose dimensional data is obtained from subsection 10.1) are positioned within the planes X, Y, and Z originating from the center of the connecting structure (hub mounting flange) 157. The deflector 200 is constrained by corner A (the trailing edge of the deflector 200 at the tip end of the deflector), corner B (the trailing edge of the deflector 200 at the hub end of the deflector), and corner C (the leading edge of the deflector 200 at the hub end of the deflector), thereby defining each corner in the X, Y, Z coordinates and thus fully defining the deflector 200 in the three-dimensional space required to obtain the dimensional data.

[0476] Figure 22B The X, Y, Z coordinates (dimensional data) of corners A, B, and C relative to the origin of the coordinate system centered on the hub flange 157 are provided. The X, Y, Z coordinates (dimensional data) of corner A are (0.66 m, 2.07 m, 44.32 m), the X, Y, Z coordinates (dimensional data) of corner B are (-0.43 m, 5.18 m, 7.89 m), and the X, Y, Z coordinates (dimensional data) of corner C are (-0.80 m, 2.69 m, 7.80 m).

[0477] To position the profiles A to E of the deflector 200 in three-dimensional space, the geometric path of the trailing edge 174 of the blade in three-dimensional space can be followed as a guide for the leading edge 208 of the deflector 200. Figure 21C The cross-sections A-A, B-B, C-C, D-D, and E-E in Figure 21D can be spaced apart at the Z intervals specified in

[0478] Furthermore, a profile twist that gradually moves away from the oncoming flow occurs between profiles A and E, totaling 1°. For example, the twist of profile A = 0.0°, the twist of profile B = 0.25°, the twist of profile C = 0.5°, the twist of profile D = 0.75°, and the twist of profile E = 1.0°. Figure 13C and Figure 13D The vertical and horizontal deflection distances between the trailing edge 174 of the deflector 200 and the leading edge 208 of the deflector, as described in subsections 8.2 - 8.3 and shown in

[0479] Combinations of elements and components

[0480] All possible combinations of the elements and components described in the specification and / or recited in the claims are contemplated and considered to be part of the present disclosure. It should be understood that all combinations of the concepts discussed in more detail herein and additional concepts (provided that these concepts are not mutually inconsistent) are contemplated as part of the inventive subject matter described herein.

[0481] Exemplary Embodiment

[0482] 1. A fluid flow turbine blade assembly, comprising: a rotor blade including a root section and a working section, the rotor blade being attached to a hub of a fluid flow turbine at the root section, wherein the working section has a leading edge and a trailing edge, and wherein the working section is configured and oriented to form a pressure surface and a suction surface, the pressure surface facing an oncoming fluid flow impinging on the rotor blade; a deflector coupled to the rotor blade and extending in a spanwise direction along at least a portion of the working section of the rotor blade, wherein the deflector has a leading edge, a trailing edge, an upstream surface facing the oncoming fluid flow, and a downstream surface facing away from the oncoming fluid flow, wherein the deflector has a substantially uniform thickness between the upstream surface and the downstream surface, wherein at least a portion of the upstream surface along at least a portion of the span of the deflector has a concave shape in a chordwise direction, and wherein the trailing edge of the deflector is located behind the trailing edge of the working section with respect to the direction of travel of the turbine blade assembly.

[0483] 2. The fluid flow turbine blade assembly according to Embodiment 1, wherein the working section of the blade is an airfoil section or a hydrofoil section.

[0484] 3. The fluid flow turbine blade assembly according to Embodiment 1 or 2, wherein at least a portion of the upstream surface has a convex shape in a chordwise direction.

[0485] 4. The fluid flow turbine blade assembly according to any one of Embodiments 1 to 3, wherein the portion of the upstream surface having a concave shape extends to the trailing edge of the deflector.

[0486] 5. The fluid flow turbine blade assembly according to Embodiment 3, wherein the portion of the upstream surface having a convex shape extends to the leading edge of the deflector.

[0487] 6. The fluid flow turbine blade assembly according to any one of Embodiments 1 to 5, wherein along at least a portion of the span of the deflector, the leading edge of the deflector is closer to the oncoming fluid flow than the trailing edge of the rotor blade.

[0488] 7. The fluid flow turbine blade assembly according to Embodiment 6, wherein along at least a portion of the span of the deflector, the trailing edge of the deflector is closer to the oncoming fluid flow than the trailing edge of the rotor blade.

[0489] 8. The fluid flow turbine blade assembly according to any one of embodiments 1 to 5, wherein along at least a portion of the span of the deflector, a leading edge of the deflector is further away from the oncoming fluid flow than a trailing edge of the rotor blade.

[0490] 9. The fluid flow turbine blade assembly according to embodiment 8, wherein along at least a portion of the span of the deflector, a trailing edge of the deflector is further away from the oncoming fluid flow than a trailing edge of the rotor blade.

[0491] 10. The fluid flow turbine blade assembly according to any one of embodiments 1 to 9, wherein a leading edge of the deflector is located behind a trailing edge of the working section with respect to a traveling direction of the turbine blade assembly.

[0492] 11. The fluid flow turbine blade assembly according to any one of embodiments 1 to 10, further comprising a connector assembly that connects the deflector to the rotor blade.

[0493] 12. The fluid flow turbine blade assembly according to embodiment 11, wherein the connector assembly includes: a tube; a deflector end flange fixedly linked to one end of the tube and the deflector; and a blade end flange fixedly linked to an opposite end of the tube and the rotor blade.

[0494] 13. The fluid flow turbine blade assembly according to embodiment 12, wherein the turbine blade assembly is attached to a hub of a rotor rotatable about a rotor axis of rotation, the turbine blade assembly is axially oriented with respect to the rotor axis of rotation, and at least a portion of the oncoming fluid flow is parallel to the rotor axis of rotation, wherein a first section of the tube defines an aerodynamic shape that tapers towards a first leading edge of the first section and towards a first trailing edge of the first section with respect to the oncoming fluid flow, and a second section of the tube defines an aerodynamic shape that tapers towards a second leading edge of the second section and towards a second trailing edge of the second section with respect to a fluid flow generated by rotation of the rotor.

[0495] 14. The fluid flow turbine blade assembly according to embodiment 13, wherein the first section is symmetric about a line bisecting the first section between the first leading edge and the first trailing edge, and the second section is symmetric about a line bisecting the second section between the second leading edge and the second trailing edge.

[0496] 15. The fluid flow turbine blade assembly according to any one of embodiments 12 to 14 includes two or more connector assemblies, each connector assembly being disposed at a different spanwise position along the turbine blade assembly, and wherein the tube of each connector assembly is shaped between its opposite ends to conform to an arc centered on the rotational axis of the fluid flow turbine and having a radius corresponding to the spanwise position of the connector assembly.

[0497] 16. The fluid flow turbine blade assembly according to any one of embodiments 1 to 15, wherein the spacing between the deflector and the rotor blade is constant across the span of the deflector.

[0498] 17. The fluid flow turbine blade assembly according to any one of embodiments 1 to 15, wherein the spacing between the deflector and the rotor blade varies across at least a portion of the span of the deflector.

[0499] 18. The fluid flow turbine blade assembly according to any one of embodiments 1 to 17, wherein at least one of the radius of curvature and the arc length of the portion of the upstream surface having the concave shape varies across at least a portion of the span of the deflector.

[0500] 19. The fluid flow turbine blade assembly according to any one of embodiments 1 to 18, wherein at least a portion of the chord extending between the leading edge and the trailing edge of the deflector is disposed outside the profile of the deflector defined between the upstream surface and the downstream surface of the deflector.

[0501] 20. The fluid flow turbine blade assembly according to embodiment 19, wherein at least 25 - 90% of the chord extending between the leading edge and the trailing edge of the deflector is disposed outside the profile of the deflector defined between the upstream surface and the downstream surface of the deflector.

[0502] 21. The fluid flow turbine blade assembly according to embodiment 20, wherein at the tip end of the deflector, at least 25 - 80% of the chord extending between the leading edge and the trailing edge of the deflector is disposed outside the profile of the deflector defined between the upstream surface and the downstream surface of the deflector, and at the hub end of the deflector, at least 65 - 90% of the chord extending between the leading edge and the trailing edge of the deflector is disposed outside the profile of the deflector defined between the upstream surface and the downstream surface of the deflector.

[0503] 22. The fluid flow turbine blade assembly according to any one of embodiments 1 to 21, wherein the spanwise curvature of the leading edge of the deflector follows the spanwise curvature of the trailing edge of the blade.

[0504] 23. The fluid flow turbine blade assembly according to any one of embodiments 1 to 22, further comprising one or more walls protruding from at least one of the upstream surface and the downstream surface of the deflector, wherein each wall extends at least partially from the leading edge of the deflector to the trailing edge of the deflector.

[0505] 24. The fluid flow turbine blade assembly according to embodiment 23, further comprising a transverse wall extending from at least one of the one or more walls, wherein the transverse wall extends along or near the trailing edge of the deflector.

[0506] 25. The fluid flow turbine blade assembly according to any one of embodiments 1 to 24, wherein the deflector comprises two or more sections, wherein each section is connected to an adjacent section by a connector, the connector comprising a top plate and a bottom plate overlapping the adjacent ends of the section and the adjacent section, and a fastener extending through the top plate and the bottom plate and the portions of the section and the adjacent section overlapped by the top plate and the bottom plate.

[0507] 26. The fluid flow turbine blade assembly according to any one of embodiments 1 to 25, wherein the deflector has a reflected mean camber line such that the center of curvature of a first portion of the reflected mean camber line is located on the downstream side of the deflector, and the center of curvature of a second portion of the reflected mean camber line is located on the upstream side of the deflector.

[0508] 27. The fluid flow turbine assembly according to any one of embodiments 1 to 26, wherein along at least a portion of the span of the deflector extending to the tip end of the deflector, both the leading edge of the deflector and the trailing edge of the deflector are closer to the oncoming flow than both the leading edge of the blade and the trailing edge of the blade.

[0509] 28. The fluid flow turbine assembly according to embodiment 27, wherein at the hub end of the deflector, at least one of the leading edge of the deflector and the trailing edge of the deflector is not closer to the oncoming flow than at least one of the leading edge of the blade and the trailing edge of the blade.

[0510] 29. The fluid flow turbine assembly according to embodiment 28, wherein the distance by which the deflector is closer to the oncoming flow than the blade continuously increases from the hub end of the deflector to the tip end of the deflector.

[0511] 30. The fluid flow turbine blade assembly according to any one of embodiments 11 to 15, wherein the connector assembly connects the deflector to the rotor blade such that the angle of attack of the deflector relative to the rotor rotation plane is fixed or such that the angle of attack of the deflector relative to the rotor rotation plane is variable.

[0512] 31. The fluid flow turbine blade assembly according to embodiment 11, wherein the connector assembly includes a variable angle connector assembly that connects the deflector to the rotor blade such that the angle of attack of the deflector relative to the rotor rotation plane is variable, and wherein the variable angle connector assembly includes: a spar having a first end fixed to an internal structure within the rotor blade and a second end pivotally connected to the deflector; a flexible shaft having a first end supported within the rotor blade for axial movement relative to the longitudinal axis of the flexible shaft and a second end pivotally connected to the deflector at a location spaced from the location where the second end of the spar is pivotally connected to the deflector; and a flexible shaft actuator coupled to the first end of the flexible shaft for effecting axial movement of the flexible shaft.

[0513] 32. The fluid flow turbine assembly according to embodiment 31, wherein the flexible shaft actuator includes: a guide tube assembly disposed within the rotor blade, the guide tube assembly including a guide tube housing and a guide tube, the guide tube housing having a guide hole within which the first end of the flexible shaft is supported, the guide tube being movable within the guide hole, wherein the first end of the flexible shaft is coupled to an end of the guide tube; a drive screw extending into a hole formed in the guide tube; a threaded collar coupled to the drive screw such that rotation of the drive screw causes corresponding axial movement of the collar along the length of the drive screw, wherein the collar is coupled to the guide tube such that axial movement of the collar is transmitted to the guide tube to cause axial movement of the guide tube within the guide hole, the axial movement of the guide tube causing corresponding axial movement of the flexible shaft; and a motor coupled to the drive screw for effecting powered rotation of the drive screw.

[0514] 33. The fluid flow turbine assembly according to embodiment 32, wherein the motor is coupled to the drive screw by a right angle drive that transmits shaft rotation generated by the motor in a first direction to rotate the drive screw and transmits shaft rotation generated by the motor in a second direction to rotate a drive shaft to transmit rotation to a flexible shaft actuator of an adjacent variable angle connector assembly.

[0515] 34. The fluid flow turbine blade assembly according to any one of embodiments 1 to 33, wherein the deflector extends in the spanwise direction along the entire span of the rotor blade including the root section and the working section.

[0516] 35. The fluid flow turbine blade assembly according to any one of embodiments 1 to 34, wherein at least a portion of the trailing edge of the deflector includes a curved section with a decreasing chord length between the leading edge and the trailing edge of the deflector, and wherein the curved section extends to the tip of the deflector.

[0517] 36. The fluid flow turbine blade assembly according to any one of embodiments 1 to 34, wherein at least a portion of the trailing edge of the deflector includes an arcuate section with an increasing chord length between the leading edge and the trailing edge of the deflector, and wherein the arcuate section extends to the tip of the deflector.

[0518] 37. A fluid flow turbine blade assembly, comprising: a rotor blade including a root section and a working section, the rotor blade being attached to a hub of a fluid flow turbine at the root section, wherein the working section has a leading edge and a trailing edge, and wherein the working section is configured and oriented to form a pressure surface and a suction surface, the pressure surface facing the oncoming fluid flow impinging on the rotor blade; a deflector coupled to the rotor blade and extending in the spanwise direction along at least a portion of the working section of the rotor blade, wherein the deflector has a leading edge, a trailing edge, an upstream surface facing the oncoming fluid flow, and a downstream surface facing away from the oncoming fluid flow, wherein at least a portion of the chord extending between the leading edge and the trailing edge of the deflector is disposed outside the profile of the deflector defined between the upstream surface and the downstream surface of the deflector, wherein at least a portion of the upstream surface along at least a portion of the span of the deflector has a concave shape in the chordwise direction, and wherein the trailing edge of the deflector is located behind the trailing edge of the working section with respect to the direction of travel of the turbine blade assembly.

[0519] 38. The fluid flow turbine blade assembly according to embodiment 37, wherein the working section of the blade is an airfoil section or a hydrofoil section.

[0520] 39. The fluid flow turbine blade assembly according to embodiment 37 or 38, wherein at least a portion of the upstream surface has a convex shape in the chordwise direction.

[0521] 40. The fluid flow turbine blade assembly according to any one of embodiments 37 to 39, wherein the portion of the upstream surface having a concave shape extends to the trailing edge of the deflector.

[0522] 41. The fluid flow turbine blade assembly according to embodiment 39, wherein the convex-shaped portion of the upstream surface extends to the leading edge of the deflector.

[0523] 42. The fluid flow turbine blade assembly according to any one of embodiments 37 to 41, wherein along at least a portion of the span of the deflector, the leading edge of the deflector is closer to the oncoming fluid flow than the trailing edge of the rotor blade.

[0524] 43. The fluid flow turbine blade assembly according to embodiment 42, wherein along at least a portion of the span of the deflector, the trailing edge of the deflector is closer to the oncoming fluid flow than the trailing edge of the rotor blade.

[0525] 44. The fluid flow turbine blade assembly according to any one of embodiments 37 to 41, wherein along at least a portion of the span of the deflector, the leading edge of the deflector is farther from the oncoming fluid flow than the trailing edge of the rotor blade.

[0526] 45. The fluid flow turbine blade assembly according to embodiment 44, wherein along at least a portion of the span of the deflector, the trailing edge of the deflector is farther from the oncoming fluid flow than the trailing edge of the rotor blade.

[0527] 46. The fluid flow turbine blade assembly according to any one of embodiments 37 to 45, wherein the leading edge of the deflector is located behind the trailing edge of the working section relative to the direction of travel of the turbine blade assembly.

[0528] 47. The fluid flow turbine blade assembly according to any one of embodiments 37 to 46, wherein at least 25 - 90% of the chord extending between the leading edge and the trailing edge of the deflector is disposed outside the profile of the deflector defined between the upstream surface and the downstream surface of the deflector.

[0529] 48. The fluid flow turbine blade assembly according to embodiment 20, wherein at the tip end of the deflector, at least 25 - 80% of the chord extending between the leading edge and the trailing edge of the deflector is disposed outside the profile of the deflector defined between the upstream surface and the downstream surface of the deflector, and at the hub end of the deflector, at least 65 - 90% of the chord extending between the leading edge and the trailing edge of the deflector is disposed outside the profile of the deflector defined between the upstream surface and the downstream surface of the deflector.

[0530] 49. The fluid flow turbine blade assembly according to any one of embodiments 37 to 48, wherein the spanwise curvature of the leading edge of the deflector follows the spanwise curvature of the trailing edge of the blade.

[0531] 50. The fluid flow turbine blade assembly according to any one of embodiments 37 to 49, further comprising one or more walls protruding from at least one of the upstream surface and the downstream surface of the deflector, wherein each wall extends at least partially from the leading edge of the deflector to the trailing edge of the deflector.

[0532] 51. The fluid flow turbine blade assembly according to embodiment 50, further comprising a transverse wall extending from at least one of the one or more walls, wherein the transverse wall extends along or near the trailing edge of the deflector.

[0533] 52. The fluid flow turbine blade assembly according to any one of embodiments 37 to 51, wherein the deflector comprises two or more sections, wherein each section is connected to an adjacent section by a connector, the connector comprising a top plate and a bottom plate overlapping the adjacent ends of the section and the adjacent section, and a fastener extending through the top plate and the bottom plate and the portions of the section and the adjacent section overlapped by the top plate and the bottom plate.

[0534] 53. The fluid flow turbine blade assembly according to any one of embodiments 37 to 52, wherein the deflector has a reflected mean camber line such that the center of curvature of a first portion of the reflected mean camber line is located on the downstream side of the deflector, and the center of curvature of a second portion of the reflected mean camber line is located on the upstream side of the deflector.

[0535] 54. The fluid flow turbine assembly according to any one of embodiments 37 to 53, wherein along at least a portion of the span of the deflector extending to the tip end of the deflector, both the leading edge of the deflector and the trailing edge of the deflector are closer to the oncoming flow than both the leading edge of the blade and the trailing edge of the blade.

[0536] 55. The fluid flow turbine assembly according to embodiment 54, wherein at the hub end of the deflector, at least one of the leading edge of the deflector and the trailing edge of the deflector is not closer to the oncoming flow than at least one of the leading edge of the blade and the trailing edge of the blade.

[0537] 56. The fluid flow turbine assembly according to embodiment 55, wherein the distance by which the deflector is closer to the oncoming flow continuously increases from the hub end of the deflector to the tip end of the deflector.

[0538] 57. The fluid flow turbine blade assembly according to any one of embodiments 32 to 56 further includes a connector assembly that connects the deflector to the rotor blade.

[0539] 58. The fluid flow turbine blade assembly according to embodiment 57, wherein the connector assembly includes: a tube; a deflector end flange fixedly linked to one end of the tube and the deflector; and a blade end flange fixedly linked to the opposite end of the tube and the rotor blade.

[0540] 59. The fluid flow turbine blade assembly according to embodiment 58, wherein the turbine blade assembly is attached to a hub of a rotor rotatable about a rotor axis of rotation, the turbine blade assembly is axially oriented with respect to the rotor axis of rotation, and at least a portion of the oncoming fluid flow is parallel to the rotor axis of rotation, wherein a first section of the tube defines an aerodynamic shape that tapers with respect to the oncoming fluid flow towards a first leading edge of the first section and towards a first trailing edge of the first section, and a second section of the tube defines an aerodynamic shape that tapers with respect to the fluid flow generated by the rotation of the rotor towards a second leading edge of the second section and towards a second trailing edge of the second section.

[0541] 60. The fluid flow turbine blade assembly according to embodiment 59, wherein the first section is symmetric about a line bisecting the first section between the first leading edge and the first trailing edge, and the second section is symmetric about a line bisecting the second section between the second leading edge and the second trailing edge.

[0542] 61. The fluid flow turbine blade assembly according to any one of embodiments 58 to 60 includes two or more connector assemblies, each connector assembly being disposed at a different spanwise position along the turbine blade assembly, and wherein the tube of each connector assembly is shaped between its opposite ends to conform to an arc centered on the axis of rotation of the fluid flow turbine and having a radius corresponding to the spanwise position of the connector assembly.

[0543] 62. The fluid flow turbine blade assembly according to any one of embodiments 37 to 61, wherein the spacing between the deflector and the rotor blade is constant across the span of the deflector.

[0544] 63. The fluid flow turbine blade assembly according to any one of embodiments 37 to 61, wherein the spacing between the deflector and the rotor blade varies across at least a portion of the span of the deflector.

[0545] 64. A fluid flow turbine blade assembly according to any one of embodiments 37 to 63, wherein at least one of a radius of curvature and an arc length of the portion of the upstream surface having the concave shape varies along at least a portion of the span of the deflector.

[0546] 65. A fluid flow turbine blade assembly according to any one of embodiments 57 to 61, wherein the connector assembly connects the deflector to the rotor blade such that an angle of attack of the deflector relative to the rotor rotation plane is fixed or such that the angle of attack of the deflector relative to the rotor rotation plane is variable.

[0547] 66. A fluid flow turbine blade assembly according to any one of embodiments 57, wherein the connector assembly includes a variable angle connector assembly that connects the deflector to the rotor blade such that an angle of attack of the deflector relative to the rotor rotation plane is variable, and wherein the variable angle connector assembly includes: a spar having a first end fixed to an internal structure within the rotor blade and a second end pivotally connected to the deflector; a flexible shaft having a first end supported within the rotor blade for axial movement relative to a longitudinal axis of the flexible shaft and a second end pivotally connected to the deflector at a location spaced from the location where the second end of the spar is pivotally connected to the deflector; and a flexible shaft actuator coupled to the first end of the flexible shaft for effecting axial movement of the flexible shaft.

[0548] 67. A fluid flow turbine assembly according to embodiment 66, wherein the flexible shaft actuator includes: a guide tube assembly disposed within the rotor blade, the guide tube assembly including a guide tube housing and a guide tube, the guide tube housing having a guide hole within which the first end of the flexible shaft is supported and the guide tube being movable within the guide hole, wherein the first end of the flexible shaft is coupled to an end of the guide tube; a drive screw extending into a hole formed in the guide tube; a threaded collar coupled to the drive screw such that rotation of the drive screw causes a corresponding axial movement of the collar along the length of the drive screw, wherein the collar is coupled to the guide tube such that the axial movement of the collar is transmitted to the guide tube to cause axial movement of the guide tube within the guide hole, the axial movement of the guide tube causing a corresponding axial movement of the flexible shaft; and a motor coupled to the drive screw for effecting powered rotation of the drive screw.

[0549] 68. The fluid flow turbine assembly according to embodiment 67, wherein the motor is coupled to the drive screw through a right angle drive, and the right angle drive transmits the shaft rotation generated by the motor in a first direction to rotate the drive screw and transmits the shaft rotation generated by the motor in a second direction to rotate a drive shaft to transmit rotation to a flexible shaft actuator of an adjacent variable angle connector assembly.

[0550] 69. The fluid flow turbine blade assembly according to any one of embodiments 37 to 68, wherein the deflector extends in a spanwise direction along the entire span of the rotor blade including the root section and the working section.

[0551] 70. The fluid flow turbine blade assembly according to any one of embodiments 37 to 69, wherein from the leading edge to the trailing edge of the deflector, the deflector has an uneven thickness between the upstream surface and the downstream surface.

[0552] 71. The fluid flow turbine blade assembly according to any one of embodiments 37 to 70, wherein at least a part of the trailing edge of the deflector includes a curved section with a decreasing chord length between the leading edge and the trailing edge of the deflector, and the curved section extends to the tip of the deflector.

[0553] 72. The fluid flow turbine blade assembly according to any one of embodiments 37 to 70, wherein at least a part of the trailing edge of the deflector includes an arcuate section with an increasing chord length between the leading edge and the trailing edge of the deflector, and the arcuate section extends to the tip of the deflector.

[0554] 73. A fluid flow turbine, comprising: a hub; a rotor including two or more turbine blade assemblies according to any one of embodiments 37 to 72 connected to the hub, wherein the rotor is rotatable about a rotor rotation axis, and each turbine blade assembly extends axially with respect to the rotor rotation axis.

[0555] 74. The fluid flow turbine according to embodiment 73, wherein the rotor rotation axis is vertically or horizontally oriented.

[0556] 75. The fluid flow turbine according to embodiment 73 or 74, including at least three of the turbine blade assemblies connected to the hub.

[0557] 76. The fluid flow turbine according to any one of embodiments 73 to 75, including: a nacelle, wherein the hub is supported by the nacelle or supported within the nacelle; a tower supporting the nacelle.

[0558] 77. The fluid flow turbine according to embodiment 76 further includes at least one of a gearbox and a generator located within the nacelle and operably coupled to the rotor.

[0559] 78. The fluid flow turbine according to embodiment 73, wherein at least a portion of the oncoming fluid flow is substantially parallel to the rotor axis of rotation.

[0560] 79. A water-driven turbine assembly includes a fluid flow turbine according to any one of embodiments 73 to 78.

[0561] 80. A wind-driven turbine assembly includes a fluid flow turbine according to any one of embodiments 73 to 78.

[0562] 81. A fluid flow turbine includes: a hub; a rotor including two or more turbine blade assemblies according to any one of embodiments 1 to 26 connected to the hub, wherein the rotor is rotatable about a rotor axis of rotation and each turbine blade assembly extends axially relative to the rotor axis of rotation.

[0563] 82. The fluid flow turbine according to embodiment 81, wherein the rotor axis of rotation is vertically or horizontally oriented.

[0564] 83. The fluid flow turbine according to embodiment 81 or 82 includes at least three of the turbine blade assemblies connected to the hub.

[0565] 84. The fluid flow turbine according to any one of embodiments 81 to 83 includes: a nacelle, wherein the hub is supported by or within the nacelle; a tower that supports the nacelle.

[0566] 85. The fluid flow turbine according to embodiment 84 further includes at least one of a gearbox and a generator located within the nacelle and operably coupled to the rotor.

[0567] 86. The fluid flow turbine according to embodiment 81, wherein at least a portion of the oncoming fluid flow is substantially parallel to the rotor axis of rotation.

[0568] 87. A water-driven turbine assembly includes a fluid flow turbine according to any one of embodiments 81 to 86.

[0569] 88. A wind-driven turbine assembly includes a fluid flow turbine according to any one of embodiments 81 to 86.

[0570] 89. A fluid flow turbine blade assembly, comprising: a rotor blade including a root section and a working section, the rotor blade being attached to a hub of a fluid flow turbine at the root section, wherein the working section has a leading edge and a trailing edge, and wherein the working section is configured and oriented to form a pressure surface and a suction surface, the pressure surface facing an oncoming fluid flow impinging on the rotor blade; a deflector coupled to the rotor blade and extending in a spanwise direction along at least a portion of the working section of the rotor blade, wherein the deflector has a leading edge, a trailing edge, an upstream surface facing the oncoming fluid flow, and a downstream surface facing away from the oncoming fluid flow, wherein the deflector is configured such that when fluid flows over the turbine blade assembly, the pressure on a region of the pressure surface of the working section that is closer to the trailing edge of the blade than to the leading edge of the blade is greater than the pressure on a similar region of a rotor blade without a deflector, and the suction on a region of the suction surface of the working section that is closer to the leading edge of the blade than to the trailing edge of the blade is greater than the suction on a similar region of a rotor blade without a deflector.

[0571] 90. The fluid flow turbine blade assembly according to embodiment 89, wherein the deflector has a substantially uniform thickness between the upstream surface and the downstream surface.

[0572] 91. The fluid flow turbine blade assembly according to embodiment 89, wherein the deflector has a non-uniform thickness between the upstream surface and the downstream surface from the leading edge of the deflector to the trailing edge of the deflector.

[0573] 92. The fluid flow turbine blade assembly according to any one of embodiments 89-91, wherein at least a portion of the upstream surface along at least a portion of the span of the deflector has a concave shape in a chordwise direction.

[0574] 93. The fluid flow turbine blade assembly according to embodiment 92, wherein the portion of the upstream surface having a concave shape extends to the trailing edge of the deflector.

[0575] 94. The fluid flow turbine blade assembly according to any one of embodiments 89-93, wherein the trailing edge of the deflector is located behind the trailing edge of the working section relative to the direction of travel of the turbine blade assembly.

[0576] 95. The fluid flow turbine blade assembly according to any one of embodiments 89-94, wherein at least a portion of a chord extending between the leading edge of the deflector and the trailing edge of the deflector is disposed outside a profile of the deflector defined between the upstream surface of the deflector and the downstream surface of the deflector.

[0577] 96. The fluid flow turbine blade assembly according to any one of embodiments 89 - 95, wherein the working section of the blade is an airfoil section or a hydrofoil section.

[0578] 97. The fluid flow turbine blade assembly according to any one of embodiments 89 - 96, wherein at least a portion of the upstream surface has a convex shape in the chordwise direction.

[0579] 98. The fluid flow turbine blade assembly according to embodiment 97, wherein the portion of the upstream surface having a convex shape extends to the leading edge of the deflector.

[0580] 99. The fluid flow turbine blade assembly according to any one of embodiments 89 to 98, wherein along at least a portion of the span of the deflector, the leading edge of the deflector is closer to the oncoming fluid flow than the trailing edge of the rotor blade.

[0581] 100. The fluid flow turbine blade assembly according to embodiment 99, wherein along at least a portion of the span of the deflector, the trailing edge of the deflector is closer to the oncoming fluid flow than the trailing edge of the rotor blade.

[0582] 101. The fluid flow turbine blade assembly according to any one of embodiments 89 to 100, wherein the leading edge of the deflector is located behind the trailing edge of the working section with respect to the direction of travel of the turbine blade assembly.

Claims

1. A fluid flow turbine blade assembly, comprising: A rotor blade including a root section and a working section, the rotor blade being attached to a hub of a fluid flow turbine at the root section, wherein the working section has a leading edge and a trailing edge, and wherein the working section is configured and oriented to form a pressure surface and a suction surface, the pressure surface facing an oncoming fluid flow impinging on the rotor blade; And A splitter plate coupled to the rotor blade and extending in a spanwise direction along at least a portion of the working section of the rotor blade, wherein the splitter plate has a leading edge, a trailing edge, an upstream surface facing the oncoming fluid flow, and a downstream surface facing away from the oncoming fluid flow, wherein the splitter plate has a substantially uniform thickness between the upstream surface and the downstream surface, wherein at least a portion of the upstream surface along at least a portion of the span of the splitter plate has a concave shape in a chordwise direction, and wherein the trailing edge of the splitter plate is located behind the trailing edge of the working section with respect to the direction of travel of the turbine blade assembly.

2. The fluid flow turbine blade assembly according to claim 1, wherein, The working section of the blade is an airfoil section or a hydrofoil section.

3. The fluid flow turbine blade assembly according to claim 1 or 2, wherein, At least a portion of the upstream surface has a convex shape in a chordwise direction.

4. The fluid flow turbine blade assembly according to any one of claims 1 to 3, wherein, The portion of the upstream surface having the concave shape extends to the trailing edge of the splitter plate.

5. The fluid flow turbine blade assembly according to claim 3, wherein, The portion of the upstream surface having the convex shape extends to the leading edge of the splitter plate.

6. The fluid flow turbine blade assembly according to any one of claims 1 to 5, wherein, Along at least a portion of the span of the splitter plate, the leading edge of the splitter plate is closer to the oncoming fluid flow than the trailing edge of the rotor blade.

7. The fluid flow turbine blade assembly according to claim 6, wherein, Along at least a portion of the span of the splitter plate, the trailing edge of the splitter plate is closer to the oncoming fluid flow than the trailing edge of the rotor blade.

8. The fluid flow turbine blade assembly according to any one of claims 1 to 5, wherein, Along at least a portion of the span of the splitter plate, the leading edge of the splitter plate is farther from the oncoming fluid flow than the trailing edge of the rotor blade.

9. The fluid flow turbine blade assembly according to claim 8, wherein, Along at least a portion of the span of the splitter plate, the trailing edge of the splitter plate is farther from the oncoming fluid flow than the trailing edge of the rotor blade.

10. The fluid flow turbine blade assembly according to any one of claims 1 to 9, wherein, The leading edge of the splitter plate is located behind the trailing edge of the working section with respect to the direction of travel of the turbine blade assembly.

11. The fluid flow turbine blade assembly according to any one of claims 1 to 10, further comprising a connector assembly connecting the splitter plate to the rotor blade.

12. The fluid flow turbine blade assembly according to claim 11, wherein, The connector assembly includes: A tube; A splitter plate end flange fixedly linked to one end of the tube and the splitter plate; and A blade end flange fixedly linked to the opposite end of the tube and the rotor blade.

13. The fluid flow turbine blade assembly according to claim 12, wherein, The turbine blade assembly is attached to a hub of a rotor capable of rotating about a rotor axis of rotation, the turbine blade assembly is axially oriented relative to the rotor axis of rotation, and at least a portion of the oncoming fluid flow is parallel to the rotor axis of rotation, wherein a first section of the tube defines an aerodynamic shape that tapers towards a first leading edge of the first section and towards a first trailing edge of the first section relative to the oncoming fluid flow, and a second section of the tube defines an aerodynamic shape that tapers towards a second leading edge of the second section and towards a second trailing edge of the second section relative to the fluid flow generated by the rotation of the rotor.

14. The fluid flow turbine blade assembly according to claim 13, wherein, The first section is symmetric about a line bisecting the first section between the first leading edge and the first trailing edge, and the second section is symmetric about a line bisecting the second section between the second leading edge and the second trailing edge.

15. The fluid flow turbine blade assembly according to any one of claims 12 to 14, comprising two or more connector assemblies, each connector assembly being disposed at a different spanwise position along the turbine blade assembly, and wherein the tube of each connector assembly is shaped between its opposite ends to conform to an arc centered on the axis of rotation of the fluid flow turbine and having a radius corresponding to the spanwise position of the connector assembly.

16. The fluid flow turbine blade assembly according to any one of claims 1 to 15, wherein, The spacing between the deflector and the rotor blade is constant across the span of the deflector.

17. The fluid flow turbine blade assembly according to any one of claims 1 to 15, wherein, The spacing between the deflector and the rotor blade varies across at least a portion of the span of the deflector.

18. The fluid flow turbine blade assembly according to any one of claims 1 to 17, wherein, At least one of the radius of curvature and the arc length of the portion of the upstream surface having the concave shape varies across at least a portion of the span of the deflector.

19. The fluid flow turbine blade assembly according to any one of claims 1 to 18, wherein, At least a portion of the chord extending between the leading edge and the trailing edge of the deflector is disposed outside the profile of the deflector defined between the upstream surface and the downstream surface of the deflector.

20. The fluid flow turbine blade assembly according to claim 19, wherein, At least 25 - 90% of the chord extending between the leading edge and the trailing edge of the deflector is disposed outside the profile of the deflector defined between the upstream surface and the downstream surface of the deflector.

21. The fluid flow turbine blade assembly according to claim 20, wherein, At the tip end of the deflector, at least 25 - 80% of the chord extending between the leading edge and the trailing edge of the deflector is disposed outside the profile of the deflector defined between the upstream surface and the downstream surface of the deflector, and at the hub end of the deflector, at least 65 - 90% of the chord extending between the leading edge and the trailing edge of the deflector is disposed outside the profile of the deflector defined between the upstream surface and the downstream surface of the deflector.

22. The fluid flow turbine blade assembly according to any one of claims 1 to 21, wherein, The spanwise curvature of the leading edge of the deflector follows the spanwise curvature of the trailing edge of the blade.

23. The fluid flow turbine blade assembly according to any one of claims 1 to 22 further includes one or more walls protruding from at least one of the upstream surface and the downstream surface of the deflector, wherein each wall extends at least partially from the leading edge of the deflector to the trailing edge of the deflector.

24. The fluid flow turbine blade assembly according to claim 23 further includes a transverse wall extending from at least one of the one or more walls, wherein the transverse wall extends along or near the trailing edge of the deflector.

25. The fluid flow turbine blade assembly according to any one of claims 1 to 24, wherein, The deflector includes two or more sections, wherein each section is connected to an adjacent section by a connector, the connector including a top plate and a bottom plate overlapping the adjacent ends of the section and the adjacent section, and a fastener extending through the top plate and the bottom plate and the portions of the section and the adjacent section overlapped by the top plate and the bottom plate.

26. The fluid flow turbine blade assembly according to any one of claims 1 to 25, wherein, The deflector has a reflected mean camber line such that the center of curvature of the first portion of the reflected mean camber line is located on the downstream side of the deflector, and the center of curvature of the second portion of the reflected mean camber line is located on the upstream side of the deflector.

27. The fluid flow turbine assembly according to any one of claims 1 to 26, wherein, Along at least a portion of the span of the deflector extending to the tip end of the deflector, both the leading edge of the deflector and the trailing edge of the deflector are closer to the oncoming flow than both the leading edge of the blade and the trailing edge of the blade.

28. The fluid flow turbine assembly according to claim 27, wherein, At the hub end of the deflector, at least one of the leading edge of the deflector and the trailing edge of the deflector is not closer to the oncoming flow than at least one of the leading edge of the blade and the trailing edge of the blade.

29. The fluid flow turbine assembly according to claim 28, wherein, The distance by which the deflector is closer to the oncoming flow than the blade continuously increases from the hub end of the deflector to the tip end of the deflector.

30. The fluid flow turbine blade assembly according to any one of claims 11 to 15, wherein, The connector assembly connects the deflector to the rotor blade such that the angle of attack of the deflector relative to the rotor rotation plane is fixed, or such that the angle of attack of the deflector relative to the rotor rotation plane is variable.

31. The fluid flow turbine blade assembly according to claim 11, wherein, The connector assembly includes a variable angle connector assembly that connects the deflector to the rotor blade such that the angle of attack of the deflector relative to the rotor rotation plane is variable, and wherein the variable angle connector assembly includes: A spar having a first end fixed to an internal structure within the rotor blade and a second end pivotally connected to the deflector; A flexible shaft having a first end supported within the rotor blade for axial movement relative to the longitudinal axis of the flexible shaft and a second end pivotally connected to the deflector at a position spaced from the position where the second end of the spar is pivotally connected to the deflector; and A flexible shaft actuator coupled to the first end of the flexible shaft for effecting axial movement of the flexible shaft.

32. The fluid flow turbine assembly according to claim 31, wherein, The flexible shaft actuator includes: A guide tube assembly is disposed within the rotor blade. The guide tube assembly includes a guide tube housing and a guide tube. The guide tube housing has a guide hole, and a first end of the flexible shaft is supported within the guide hole. The guide tube is capable of moving within the guide hole, wherein the first end of the flexible shaft is coupled to an end of the guide tube; A drive screw extends into a hole formed in the guide tube; A threaded collar is coupled to the drive screw such that rotation of the drive screw causes corresponding axial movement of the collar along the length of the drive screw. The collar is coupled to the guide tube such that the axial movement of the collar is transmitted to the guide tube to cause axial movement of the guide tube within the guide hole. The axial movement of the guide tube causes corresponding axial movement of the flexible shaft; and A motor is coupled to the drive screw for effecting powered rotation of the drive screw.

33. The fluid flow turbine assembly according to claim 32, wherein, The motor is coupled to the drive screw by a right-angle drive that transmits shaft rotation generated by the motor in a first direction to rotate the drive screw and transmits shaft rotation generated by the motor in a second direction to rotate a drive shaft to transmit rotation to a flexible shaft actuator of an adjacent variable angle connector assembly.

34. A fluid flow turbine blade assembly according to any one of claims 1 to 33, wherein, The deflector extends in the spanwise direction along the entire span of the rotor blade including the root section and the working section.

35. The fluid flow turbine blade assembly according to any one of claims 1 to 34, wherein, At least a portion of the trailing edge of the deflector includes a curved section where the chord length decreases between the leading edge and the trailing edge of the deflector, wherein the curved section extends to the tip of the deflector.

36. The fluid flow turbine blade assembly according to any one of claims 1 to 34, wherein, At least a portion of the trailing edge of the deflector includes an arcuate section where the chord length increases between the leading edge and the trailing edge of the deflector, wherein the arcuate section extends to the tip of the deflector.

37. A fluid flow turbine blade assembly, comprising: A rotor blade including a root section and a working section. The rotor blade is attached to a hub of a fluid flow turbine at the root section. The working section has a leading edge and a trailing edge, and the working section is configured and oriented to form a pressure surface and a suction surface, the pressure surface facing the oncoming fluid flow impinging on the rotor blade; and A deflector coupled to the rotor blade and extending in the spanwise direction along at least a portion of the working section of the rotor blade. The deflector has a leading edge, a trailing edge, an upstream surface facing the oncoming fluid flow, and a downstream surface facing away from the oncoming fluid flow. At least a portion of the chord extending between the leading edge and the trailing edge of the deflector is disposed outside the profile of the deflector defined between the upstream surface and the downstream surface of the deflector. At least a portion of the upstream surface along at least a portion of the span of the deflector has a concave shape in the chordwise direction, and the trailing edge of the deflector is located behind the trailing edge of the working section with respect to the direction of travel of the turbine blade assembly.

38. The fluid flow turbine blade assembly according to claim 37, wherein, The working section of the blade is an airfoil section or a hydrofoil section.

39. The fluid flow turbine blade assembly according to claim 37 or 38, wherein, At least a portion of the upstream surface has a convex shape in the chordwise direction.

40. The fluid flow turbine blade assembly according to any one of claims 37 to 39, wherein, The portion of the upstream surface having a concave shape extends to the trailing edge of the deflector.

41. The fluid flow turbine blade assembly according to claim 39, wherein, The portion of the upstream surface having a convex shape extends to the leading edge of the deflector.

42. The fluid flow turbine blade assembly according to any one of claims 37 to 41, wherein, Along at least a portion of the span of the deflector, the leading edge of the deflector is closer to the oncoming fluid flow than the trailing edge of the rotor blade.

43. The fluid flow turbine blade assembly according to claim 42, wherein, Along at least a portion of the span of the deflector, the trailing edge of the deflector is closer to the oncoming fluid flow than the trailing edge of the rotor blade.

44. The fluid flow turbine blade assembly according to any one of claims 37 to 41, wherein, Along at least a portion of the span of the deflector, the leading edge of the deflector is farther from the oncoming fluid flow than the trailing edge of the rotor blade.

45. The fluid flow turbine blade assembly according to claim 44, wherein, Along at least a portion of the span of the deflector, the trailing edge of the deflector is farther from the oncoming fluid flow than the trailing edge of the rotor blade.

46. The fluid flow turbine blade assembly according to any one of claims 37 to 45, wherein, The leading edge of the deflector is located behind the trailing edge of the working section relative to the direction of travel of the turbine blade assembly.

47. The fluid flow turbine blade assembly according to any one of claims 37 to 46, wherein, At least 25 - 90% of the chord extending between the leading edge and the trailing edge of the deflector is disposed outside of the profile of the deflector defined between the upstream surface and the downstream surface of the deflector.

48. The fluid flow turbine blade assembly according to claim 20, wherein, At the tip end of the deflector, at least 25 - 80% of the chord extending between the leading edge and the trailing edge of the deflector is disposed outside of the profile of the deflector defined between the upstream surface and the downstream surface of the deflector, and at the hub end of the deflector, at least 65 - 90% of the chord extending between the leading edge and the trailing edge of the deflector is disposed outside of the profile of the deflector defined between the upstream surface and the downstream surface of the deflector.

49. The fluid flow turbine blade assembly according to any one of claims 37 to 48, wherein, The spanwise curvature of the leading edge of the deflector follows the spanwise curvature of the trailing edge of the blade.

50. The fluid flow turbine blade assembly according to any one of claims 37 to 49, further comprising one or more walls projecting from at least one of the upstream surface and the downstream surface of the deflector, wherein each wall extends at least partially from the leading edge of the deflector to the trailing edge of the deflector.

51. The fluid flow turbine blade assembly according to claim 50, further comprising a transverse wall extending from at least one of the one or more walls, wherein the transverse wall extends along or adjacent to the trailing edge of the deflector.

52. The fluid flow turbine blade assembly according to any one of claims 37 to 51, wherein, The deflector includes two or more sections, wherein each section is connected to an adjacent section by a connector, the connector including a top plate and a bottom plate overlapping the adjacent ends of the section and the adjacent section, and a fastener extending through the top plate and the bottom plate and portions of the section and the adjacent section overlapped by the top plate and the bottom plate.

53. The fluid flow turbine blade assembly according to any one of claims 37 to 52, wherein The deflector has a reflected mean camber line such that the center of curvature of a first portion of the reflected mean camber line is located on the downstream side of the deflector, and the center of curvature of a second portion of the reflected mean camber line is located on the upstream side of the deflector.

54. The fluid flow turbine assembly according to any one of claims 37 to 53, wherein, Along at least a portion of the span of the flow deflector extending to the tip end of the flow deflector, both the leading edge and the trailing edge of the flow deflector are closer to the oncoming flow than both the leading edge and the trailing edge of the blade.

55. The fluid flow turbine assembly according to claim 54, wherein, At the hub end of the flow deflector, at least one of the leading edge and the trailing edge of the flow deflector is not closer to the oncoming flow than at least one of the leading edge and the trailing edge of the blade.

56. The fluid flow turbine assembly according to claim 55, wherein, The distance by which the flow deflector is closer to the oncoming flow than the blade continuously increases from the hub end to the tip end of the flow deflector.

57. The fluid flow turbine blade assembly according to any one of claims 32 to 56, further comprising a connector assembly connecting the flow deflector to the rotor blade.

58. The fluid flow turbine blade assembly according to claim 57, wherein, The connector assembly includes: a tube; a flow deflector end flange fixedly linked to one end of the tube and the flow deflector; and a blade end flange fixedly linked to the opposite end of the tube and the rotor blade.

59. The fluid flow turbine blade assembly according to claim 58, wherein, The turbine blade assembly is attached to a hub of a rotor rotatable about a rotor axis of rotation, the turbine blade assembly is axially oriented relative to the rotor axis of rotation, and at least a portion of the oncoming fluid flow is parallel to the rotor axis of rotation, wherein a first section of the tube defines an aerodynamic shape that tapers towards a first leading edge of the first section and towards a first trailing edge of the first section relative to the oncoming fluid flow, and a second section of the tube defines an aerodynamic shape that tapers towards a second leading edge of the second section and towards a second trailing edge of the second section relative to the fluid flow generated by the rotation of the rotor.

60. The fluid flow turbine blade assembly according to claim 59, wherein, The first section is symmetric about a line bisecting the first section between the first leading edge and the first trailing edge, and the second section is symmetric about a line bisecting the second section between the second leading edge and the second trailing edge.

61. The fluid flow turbine blade assembly according to any one of claims 58 to 60, including two or more connector assemblies, each connector assembly being disposed at a different spanwise position along the turbine blade assembly, and wherein the tube of each connector assembly is shaped between its opposite ends to conform to an arc centered on the axis of rotation of the fluid flow turbine and having a radius corresponding to the spanwise position of the connector assembly.

62. The fluid flow turbine blade assembly according to any one of claims 37 to 61, wherein, The spacing between the flow deflector and the rotor blade is constant across the span of the flow deflector.

63. The fluid flow turbine blade assembly according to any one of claims 37 to 61, wherein, The spacing between the flow deflector and the rotor blade varies across at least a portion of the span of the flow deflector.

64. The fluid flow turbine blade assembly according to any one of claims 37 to 63, wherein, At least one of the radius of curvature and the arc length of the portion of the upstream surface having the concave shape varies across at least a portion of the span of the flow deflector.

65. The fluid flow turbine blade assembly according to any one of claims 57 to 61, wherein, The connector assembly connects the deflector to the rotor blade such that the angle of attack of the deflector relative to the rotor rotation plane is fixed or such that the angle of attack of the deflector relative to the rotor rotation plane is variable.

66. The fluid flow turbine blade assembly according to any one of claims 57, wherein, The connector assembly includes a variable angle connector assembly that connects the deflector to the rotor blade such that the angle of attack of the deflector relative to the rotor rotation plane is variable, and wherein the variable angle connector assembly includes: A spar having a first end fixed to an internal structure within the rotor blade and a second end pivotally connected to the deflector; A flexible shaft having a first end supported within the rotor blade for axial movement relative to the longitudinal axis of the flexible shaft and a second end pivotally connected to the deflector at a location spaced from the location where the second end of the spar is pivotally connected to the deflector; and A flexible shaft actuator coupled to the first end of the flexible shaft for effecting axial movement of the flexible shaft.

67. The fluid flow turbine assembly according to claim 66, wherein, The flexible shaft actuator includes: A guide tube assembly disposed within the rotor blade, the guide tube assembly including a guide tube housing and a guide tube, the guide tube housing having a guide hole, the first end of the flexible shaft being supported within the guide hole, the guide tube being movable within the guide hole, wherein the first end of the flexible shaft is coupled to an end of the guide tube; A drive screw extending into a hole formed in the guide tube; A threaded collar coupled to the drive screw such that rotation of the drive screw causes corresponding axial movement of the collar along the length of the drive screw, wherein the collar is coupled to the guide tube such that axial movement of the collar is transmitted to the guide tube to cause axial movement of the guide tube within the guide hole, the axial movement of the guide tube causing corresponding axial movement of the flexible shaft; and A motor coupled to the drive screw for effecting powered rotation of the drive screw.

68. The fluid flow turbine assembly according to claim 67, wherein, The motor is coupled to the drive screw by a right angle drive that transmits shaft rotation generated by the motor in a first direction to rotate the drive screw and transmits shaft rotation generated by the motor in a second direction to rotate a drive shaft to transmit rotation to the flexible shaft actuator of an adjacent variable angle connector assembly.

69. The fluid flow turbine blade assembly according to any one of claims 37 to 68, wherein, The deflector extends spanwise along the entire span of the rotor blade including the root section and the working section.

70. The fluid flow turbine blade assembly according to any one of claims 37 to 69, wherein, From the leading edge of the deflector to the trailing edge of the deflector, the deflector has an uneven thickness between the upstream surface and the downstream surface.

71. A fluid flow turbine blade assembly according to any one of claims 37 to 70, wherein, At least a portion of the trailing edge of the deflector includes a curved section where the chord length decreases between the leading edge of the deflector and the trailing edge of the deflector, wherein the curved section extends to the tip of the deflector.

72. The fluid flow turbine blade assembly according to any one of claims 37 to 70, wherein, At least a portion of the trailing edge of the deflector includes an arcuate section that extends to the tip of the deflector and has an increasing chord length between the leading edge and the trailing edge of the deflector, wherein the arcuate section extends to the tip of the deflector.

73. A fluid flow turbine, comprising: a hub; and a rotor including two or more turbine blade assemblies according to any one of claims 37 to 72 connected to the hub, wherein the rotor is rotatable about a rotor axis of rotation and each turbine blade assembly extends axially relative to the rotor axis of rotation.

74. The fluid flow turbine according to claim 73, wherein, The rotor axis of rotation is vertically or horizontally oriented.

75. The fluid flow turbine according to claim 73 or 74, including at least three of the turbine blade assemblies connected to the hub.

76. The fluid flow turbine according to any one of claims 73 to 75, including: a nacelle, wherein the hub is supported by or within the nacelle; and a tower that supports the nacelle.

77. The fluid flow turbine according to claim 76, further including at least one of a gearbox and a generator located within the nacelle and operably coupled to the rotor.

78. The fluid flow turbine according to claim 73, wherein, At least a portion of the oncoming fluid flow is substantially parallel to the rotor axis of rotation.

79. A water-driven turbine assembly, including a fluid flow turbine according to any one of claims 73 to 78.

80. A wind-driven turbine assembly, including a fluid flow turbine according to any one of claims 73 to 78.

81. A fluid flow turbine, comprising: a hub; and a rotor including two or more turbine blade assemblies according to any one of claims 1 to 26 connected to the hub, wherein the rotor is rotatable about a rotor axis of rotation and each turbine blade assembly extends axially relative to the rotor axis of rotation.

82. The fluid flow turbine according to claim 81, wherein, The rotor axis of rotation is vertically or horizontally oriented.

83. The fluid flow turbine according to claim 81 or 82, including at least three of the turbine blade assemblies connected to the hub.

84. The fluid flow turbine according to any one of claims 81 to 83, including: a nacelle, wherein the hub is supported by or within the nacelle; and a tower that supports the nacelle.

85. The fluid flow turbine according to claim 84, further including at least one of a gearbox and a generator located within the nacelle and operably coupled to the rotor.

86. The fluid flow turbine according to claim 81, wherein, At least a portion of the oncoming fluid flow is substantially parallel to the rotor axis of rotation.

87. A water-driven turbine assembly, including a fluid flow turbine according to any one of claims 81 to 86.

88. A wind-driven turbine assembly, including a fluid flow turbine according to any one of claims 81 to 86.

89. A fluid flow turbine blade assembly, comprising: A rotor blade, the rotor blade including a root section and a working section, the rotor blade being attached to a hub of a fluid flow turbine at the root section, wherein the working section has a leading edge and a trailing edge, and wherein the working section is configured and oriented to form a pressure surface and a suction surface, the pressure surface facing the oncoming fluid flow impinging on the rotor blade; and A deflector, the deflector being coupled to the rotor blade and extending in a spanwise direction along at least a portion of the working section of the rotor blade, wherein the deflector has a leading edge, a trailing edge, an upstream surface facing the oncoming fluid flow, and a downstream surface facing away from the oncoming fluid flow, wherein the deflector is configured such that when fluid flows over the turbine blade assembly, the pressure on a region of the pressure surface of the working section that is closer to the trailing edge of the blade than to the leading edge of the blade is greater than the pressure on a similar region of a rotor blade without a deflector, and the suction on a region of the suction surface of the working section that is closer to the leading edge of the blade than to the trailing edge of the blade is greater than the suction on a similar region of a rotor blade without a deflector.

90. The fluid flow turbine blade assembly according to claim 89, wherein, The deflector has a substantially uniform thickness between the upstream surface and the downstream surface.

91. The fluid flow turbine blade assembly according to claim 89, wherein, From the leading edge of the deflector to the trailing edge of the deflector, the deflector has a non-uniform thickness between the upstream surface and the downstream surface.

92. The fluid flow turbine blade assembly according to any one of claims 89-91, wherein, At least a portion of the upstream surface along at least a portion of the span of the deflector has a concave shape in the chordwise direction.

93. The fluid flow turbine blade assembly according to claim 92, wherein, The portion of the upstream surface having the concave shape extends to the trailing edge of the deflector.

94. The fluid flow turbine blade assembly according to any one of claims 89 - 93, wherein, The trailing edge of the deflector is located behind the trailing edge of the working section with respect to the direction of travel of the turbine blade assembly.

95. The fluid flow turbine blade assembly according to any one of claims 89 - 94, wherein, At least a portion of the chord extending between the leading edge and the trailing edge of the deflector is disposed outside the profile of the deflector defined between the upstream surface and the downstream surface of the deflector.

96. A fluid flow turbine blade assembly according to any one of claims 89 - 95, wherein, The working section of the blade is an airfoil section or a hydrofoil section.

97. The fluid flow turbine blade assembly according to any one of claims 89-96, wherein, At least a portion of the upstream surface has a convex shape in the chordwise direction.

98. The fluid flow turbine blade assembly according to claim 97, wherein, The portion of the upstream surface having the convex shape extends to the leading edge of the deflector.

99. A fluid flow turbine blade assembly according to any one of claims 89 to 98, wherein, Along at least a portion of the span of the deflector, the leading edge of the deflector is closer to the oncoming fluid flow than the trailing edge of the rotor blade.

100. The fluid flow turbine blade assembly according to claim 99, wherein, Along at least a portion of the span of the deflector, the trailing edge of the deflector is closer to the oncoming fluid flow than the trailing edge of the rotor blade.

101. A fluid flow turbine blade assembly according to any one of claims 89 to 100, wherein, The leading edge of the deflector is located behind the trailing edge of the working section with respect to the direction of travel of the turbine blade assembly.

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