Turbine blade with auxiliary deflector

Abstract

A fluid flow blade assembly for a turbine rotor includes a blade and a deflector extending spanwise along at least a portion of the blade. At least a portion of the upstream surface of the deflector along at least a portion of the span of the deflector has a concave shape in the chordwise direction such that at least a portion of a chord line between the leading and trailing edges of the deflector is located outside a profile defined between the upstream and downstream surfaces of the deflector. The deflector has a substantially uniform thickness or a chordwise varying thickness between the upstream and downstream surfaces. The deflector modifies fluid flow across the blade to increase the blade's contribution to the overall torque generated by the assembly such that, with the torque contribution of the deflector, the overall torque of the assembly exceeds the overall torque that would be generated by the blade alone without the benefit of the deflector.

Description

[Technical Field]

[0001] (CROSS-REFERENCE TO RELATED APPLICATIONS) This application claims the benefit under 35 U.S.C. § 119(e) of the filing date of U.S. Provisional Patent Application No. 63 / 409,479, filed September 23, 2022, the disclosure of which is incorporated herein by reference.

[0002] The present disclosure relates to performance improvements in turbine blades for wind and water turbines. In particular, the present disclosure relates to a turbine blade assembly including one or more deflectors, which may be arranged as single or multiple deflector assemblies, that are either fixedly or operably (adjustably) coupled to an associated turbine blade and are configured to increase the volume of fluid passing across the pressure and suction sides of the associated turbine blade and / or modify the fluid flow and resulting pressure distribution adjacent the surface. The upstream or pressure surface of the deflector includes a concave surface that begins at the trailing edge of the deflector and transitions to a convex surface or linear section that terminates at the leading edge of the deflector. The deflector may be of uniform or variable thickness between its leading and trailing edges. Each deflector is arranged with its leading edge aft of the leading edge of the associated turbine blade relative to the direction of blade travel, and the trailing edge of at least a portion of the deflector may be positioned closer to the oncoming fluid flow (wind or water) than the trailing edge of the blade. One or more deflectors may be arranged on the pressure side, suction side, or both sides of each blade. One or more deflectors may span the entire length of the associated blade, or any portion thereof. [Background technology]

[0003] Wind and hydro turbine blade design has remained relatively unchanged in recent years, with only minor performance improvements over the past few decades. As a result, the industry has resorted to making turbine blades larger to increase power output. This creates manufacturing, shipping, and installation challenges with wind turbine blades weighing over 40 tons each, often requiring months to transport from their manufacturing site to their deployment site. Logistical planning of up to one year for the transportation of a single 32-ton blade is not uncommon. Furthermore, the logistical complexities of transporting such blades from their manufacturing site to their deployment site can, in some cases, result in wind turbine projects becoming economically unviable. Additionally, despite extensive research and design efforts, the turbine industry has made only minor improvements in blade performance over the decades. As a result, manufacturers have resorted to designing and producing ever-larger rotor diameters with taller towers, thus exacerbating public resistance to the transportation, assembly, and deployment of industrial-scale wind turbines. Water turbine blade design has also been hampered by a lack of substantial performance improvements, thus limiting the locations for economically viable projects that could otherwise be reliably powered via continuous water flow. Summary of the Invention [Means for solving the problem]

[0004] The following presents a simplified summary in order to provide a basic understanding of some aspects described herein. This summary is not an extensive overview of the claimed subject matter. It is not intended to identify key or critical elements or delineate the scope of the claimed subject matter. Its sole purpose is to present some concepts in a simplified form as a prelude to the more detailed description that is presented later.

[0005] Aspects of the present disclosure are embodied in a rotor that may be part of a wind-driven or water-driven turbine and may include a deflector that is located closer to the oncoming flow than the turbine blade to which the deflector is attached and deflects additional fluid flow across such turbine blade.

[0006] According to other aspects, the deflector may be configured with wind turbines, water turbines, including, but not limited to, hydrodynamic axial flow turbines, in different axial orientations, including, but not limited to, horizontal axis, tilted axis, and vertical axis.

[0007] According to another aspect, the deflector may be configured to span the entire length of the associated rotor blade, including the blade root.

[0008] According to another aspect, the deflector may be configured to affect the entire airfoil or hydrofoil portion of an associated wind or water rotor blade.

[0009] According to another aspect, the deflector may be configured to affect a portion of an airfoil or hydrofoil portion of a wind or water rotor blade.

[0010] According to another aspect, the deflector may be fixedly coupled to the wind or water rotor blade.

[0011] According to another aspect, the deflector may be adjustably connected to a wind or water turbine blade, whereby the deflector angle of attack may be varied.

[0012] According to another aspect, the deflector includes a leading edge, a trailing edge, a tip end edge, and a root end edge, each of which may have a different or similar geometric shape.

[0013] According to another aspect, the shape of the deflector's circumference around its leading edge, tip end, trailing edge, and hub end may be generally quadrilateral or trapezoidal.

[0014] According to another aspect, the thickness of the deflector may be substantially uniform.

[0015] According to another aspect, the deflector may have a variety of thicknesses.

[0016] According to another aspect, the deflector may include an integral wing portion.

[0017] According to another aspect, the deflector may include an integral hydrofoil portion.

[0018] According to another aspect, the deflector may twist along its spanwise length.

[0019] According to another aspect, the deflector may have a trailing concave surface on the pressure surface and a corresponding convex surface on the suction surface near its trailing edge.

[0020] According to another aspect, the geometry, such as the radius of curvature and / or arc length, of the trailing concave surface may vary from the tip end of the deflector to the hub end of the deflector.

[0021] According to another aspect, the deflector may have a leading convex surface on the pressure surface and a corresponding concave surface on the suction surface near its leading edge.

[0022] According to another aspect, the deflector may have a convex leading surface near its leading edge.

[0023] According to another aspect, the deflector may have a mean camber line that is recurved.

[0024] According to another aspect, the geometry, such as the radius of curvature and / or arc length, of the leading convex surface may vary from the tip end of the deflector to the hub end of the deflector.

[0025] According to another aspect, the deflector leading edge may have a geometry that generally follows the trailing edges of the individual blades.

[0026] According to another aspect, the deflector may have a chord that is located outside the profile of the deflector.

[0027] According to another aspect, the deflector may have a curved tip end.

[0028] According to another aspect, the deflector may be positioned subsequent to the associated blade.

[0029] According to another aspect, the deflector may be positioned with the leading edge aft of the leading edge of the associated blade.

[0030] According to another aspect, the deflectors may be skewed so that the tip end of the deflector is closer to the individual blades and the hub end of the deflector is further from the individual blades.

[0031] According to another aspect, more than one deflector may be positioned closer to the flow than the individual blades.

[0032] According to another aspect, the deflector may be positioned farther from the flow than the individual blades.

[0033] According to another aspect, the deflector may have a fluid wall that protrudes from its pressure or suction surface.

[0034] According to another aspect, the deflector may be comprised of multiple sections that, when assembled, are the mirror image of a deflector fabricated as a monolithic structure.

[0035] According to another aspect, the deflectors may be connected by a multi-part connector.

[0036] According to another aspect, the deflector may have a fixed angle of attack.

[0037] Other features and characteristics of the subject matter of the present disclosure, as well as the method of operation, function and combination of parts of associated elements of construction, and economies of manufacture, will become more apparent upon consideration of the following description and appended claims, with reference to the accompanying drawings, all of which form a part of this specification and in which like reference numerals designate corresponding parts in the various views.

[0038] (Incorporated by reference) All publications, patents, and patent applications mentioned in this specification are herein incorporated by reference to the same extent as if each individual publication, patent, or patent application was specifically and individually indicated to be incorporated by reference. [Brief explanation of the drawings]

[0039] The accompanying drawings, which are incorporated in and form a part of this specification, illustrate various embodiments of the presently disclosed subject matter, in which like reference numbers indicate identical or functionally similar elements.

[0040] [Figure 1A] FIG. 1A is an isometric view of a three-bladed wind turbine.

[0041] [Figure 1B] FIG. 1B is a cutaway side isometric view of a wind turbine nacelle with a cutaway section revealing the gearbox and generator.

[0042] [Figure 2A] FIG. 2A is a front isometric view of a wind turbine blade with a detailed view of the blade profile near the tip, center, and hub ends of the blade.

[0043] [Figure 2B] FIG. 2B is a rear isometric view of a wind turbine blade.

[0044] [Figure 2C]FIG. 2C is a cross-sectional view of a typical wind turbine blade near the hub end, revealing the internal components.

[0045] [Figure 2D] FIG. 2D is a schematic profile diagram of a typical wind turbine blade showing the relative airflow and lift and drag forces on the blade.

[0046] [Figure 2E] FIG. 2E is a cross-sectional profile view of a typical wind turbine blade near the tip end showing areas of interest on the pressure and suction sides of the blade.

[0047] [Figure 2F] FIG. 2F is a cross-sectional profile view of a typical wind turbine blade near the hub end showing the useful areas on the pressure and suction sides of the blade, with an enlarged detail of the trailing edge at higher angles of attack creating additional useful areas.

[0048] [Figure 2G] FIG. 2G is a schematic profile diagram of a cross section of a typical wind turbine blade showing the tilt angles and force types on useful areas on the pressure and suction sides of the blade, with an enlarged detail of the suction side tilt angle.

[0049] [Figure 3] FIG. 3 is an isometric view of a three-bladed water turbine with a cutaway section of the nacelle revealing the gearbox and generator assembly.

[0050] [Figure 4A] FIG. 4A is a front isometric view of a typical water turbine blade, with a detailed view of the blade profile near the tip, center, and hub end of the blade.

[0051] [Figure 4B] FIG. 4B is a rear isometric view of a water turbine blade.

[0052] [Figure 5A] FIG. 5A is a front view of a wind turbine in which deflectors are coupled to the turbine blades and positioned to affect the entire airfoil section of each blade.

[0053] [Figure 5B] 5B is a front view of a rotor consisting of a deflector / blade assembly, with dashed lines depicting the boundaries of the outer swept volume, transition swept volume, and common swept volume, and an enlarged side detailed schematic cutaway view depicting the spaces between the volumes and areas for oncoming fluid flow. For clarity, the detailed view is not drawn to scale, and the blades and deflectors are not shown in their individual three-dimensional spaces.

[0054] [Figure 6] FIG. 6 is a front view of a wind turbine in which partial span deflectors are coupled to the turbine blades and positioned to affect a portion of the airfoil section of each blade.

[0055] [Figure 7] FIG. 7 is a front view of a water turbine in which deflectors are coupled to the turbine blades and positioned to affect the entire hydrofoil section of each blade.

[0056] [Figure 8] FIG. 8 is a front view of a water turbine in which partial span deflectors are coupled to the turbine blades and positioned to affect a portion of the hydrofoil section of each blade.

[0057] [Figure 9A] FIG. 9A is a front isometric view of the deflector, excluding any structure connecting the deflector to the blades, with enlarged (i) cross-sectional views of the tip end and center section, (ii) an end view of the hub end, and (iii) a cutaway detail view of the front of the tip end.

[0058] [Figure 9B] FIG. 9B is a rear view of the deflector / blade assembly, excluding any structure connecting the deflector to the blade, showing the deflector leading edge curvature matching the blade trailing edge curvature.

[0059] [Figure 9C] FIG. 9C is a cross-sectional view of the tip end of an alternative embodiment of a deflector with exaggerated convexity to more easily show the convex geometry.

[0060] [Figure 9D] FIG. 9D is a hub end view of an alternative embodiment of a deflector with exaggerated convexity to more easily show the convex geometry.

[0061] [Figure 9E] FIG. 9E is a front view of the deflector / blade assembly with five detailed profile views starting at the deflector tip end and ending at the deflector hub end.

[0062] [Figure 9F] FIG. 9F is a side view of the deflector and blade profile at the tip end of the deflector showing the angle of attack and position of the deflector relative to the blade.

[0063] [Figure 9G] FIG. 9G is a side view of the deflector and blade profile at 25 percent distance from the tip end of the deflector showing the angle of attack and position of the deflector relative to the blade.

[0064] [Figure 9H] FIG. 9H is a side view of the deflector and blade profile at a point midway between the deflector tip end and hub end, showing the angle of attack and position of the deflector relative to the blade.

[0065] [Figure 9I]FIG. 9I is a side view of the deflector and blade profile at 25 percent distance from the deflector hub end, showing the angle of attack and position of the deflector relative to the blade.

[0066] [Figure 9J] FIG. 9J is a side view of the deflector and blade profile at the deflector hub end, showing the angle of attack and position of the deflector relative to the blade.

[0067] [Figure 9K] FIG. 9K is a rear view of an embodiment of a deflector / blade assembly with a fixedly coupled connector assembly and associated rotational travel path about the rotor axis of rotation.

[0068] [Figure 9L] FIG. 9L is a cutaway enlarged view of the rear of the deflector / blade assembly and single, fixedly coupled connector assembly, with an enlarged detailed rear isometric view of the curved leading and trailing edges of the connector assembly cooperating with rotational flow.

[0069] [Figure 9M] FIG. 9M is a side view of a fixed deflector connector assembly including a deflector end flange, connector tube, and blade end flange, with (i) a detailed cross-sectional view of the leading and trailing edges of the connector tube relative to the rotational flow, and (ii) an enlarged top cross-sectional view of the leading and trailing edges of the connector tube relative to the deflector / blade assembly in a static position.

[0070] [Figure 9N] FIG. 9N is a cutaway hub end side view of the deflector / blade assembly with a cross section revealing one embodiment of a connector assembly fixedly coupled within the deflector and blade.

[0071] [Figure 10A]FIG. 10A is a side view of the flow trajectory lines impinging on the blade pressure surface without a deflector while the blade is in a static position and exposed to a 2.0 m / s wind.

[0072] [Figure 10B] FIG. 10B is a side view of the flow trajectory lines impinging on the blade pressure surfaces and deflectors of the deflector / blade assembly while the deflector / blade assembly is in a static position and exposed to a 2.0 m / sec wind.

[0073] [Figure 10C] FIG. 10C is a side view of a pressure plot around the upstream and downstream surfaces of the blade of FIG. 10A.

[0074] [Figure 10D] FIG. 10D is a side view of a pressure plot around the upstream and downstream surfaces of the deflector / blade assembly of FIG. 10B.

[0075] [Figure 10E] FIG. 10E is an enlarged side isometric view of the cross section of the blade of FIG. 10A showing the surface pressures on the upstream and downstream surfaces of the cross section, with pressure regions displayed on the outside of the upstream surface and on the inside of the downstream surface.

[0076] [Figure 10F] FIG. 10F is an enlarged side isometric view of a cross section of the blade of FIG. 10B showing the surface pressure on the pressure and suction surfaces of the cross section (deflectors not shown in the figure).

[0077] [Figure 11A] FIG. 11A is a side view of apparent velocity flow trajectories around a cross section of the blade surface near the tip of a rotating blade in a 3.5 m / s wind without the benefit of a deflector.

[0078] [Figure 11B]FIG. 11B is a side view of apparent velocity flow trajectories around a cross section of the blade and deflector surface near the tip of a rotating deflector / blade assembly in a 3.5 m / s wind with the benefit of the deflector, including illustrative high and low pressure regions.

[0079] [Figure 11C] FIG. 11C is a side view of a pressure plot around the upstream and downstream surfaces of the blade of FIG. 11A.

[0080] [Figure 11D] FIG. 11D is a side view of a pressure plot around the upstream and downstream surfaces of the deflector / blade assembly of FIG. 11B.

[0081] [Figure 11E] FIG. 11E is a front view showing the upstream surface of the blade without the benefit of a deflector, with the pressure field and associated fluid pressure shown in a 3.5 m / s wind, with an enlarged detailed profile view of the blade near the tip end.

[0082] [Figure 11F] FIG. 11F is a front view showing the upstream surface of the blade of the deflector / blade assembly, with the pressure fields and associated fluid pressures shown in a 3.5 m / s wind (deflector not shown).

[0083] [Figure 11G] FIG. 11G is a rear view showing the downstream surface of the blade without the benefit of a deflector, with the pressure field and associated fluid pressure shown in a 3.5 m / s wind.

[0084] [Figure 11H] FIG. 11H is a rear view showing the downstream surface of the blade of the deflector / blade assembly with the pressure fields and associated fluid pressures shown in a 3.5 / m sec wind (although the deflector is not shown in the figure).

[0085] [Figure 11I] FIG. 11I is an enlarged side isometric view of cross section "11I" of the blade of FIGS. 11E and 11G showing the surface pressures on the upstream and downstream surfaces of the cross section.

[0086] [Figure 11J] FIG. 11J is an enlarged side isometric view of section "11J" of the blade of FIGS. 11F and 11H showing the surface pressure on the pressure and suction surfaces of the section (deflectors not shown in the figure).

[0087] [Figure 12A] FIG. 12A is a side view of a pressure plot around a cross section of the blade surface near the tip of a rotating blade in a 13 m / s wind without the benefit of a deflector.

[0088] [Figure 12B] FIG. 12B is a side view of a pressure plot around a cross section of the blade and deflector surface near the tip of a rotating deflector / blade assembly in a 13 m / s wind with the benefit of a deflector.

[0089] [Figure 12C] FIG. 12C is a front view showing the upstream surface of the blade without the benefit of a deflector, with the pressure field and associated fluid pressure shown in a 13 m / s wind, with an enlarged detailed profile view of the blade near the tip end.

[0090] [Figure 12D] FIG. 12D is a front view showing the upstream surface of the blade of a deflector / blade assembly including a deflector (although the deflector is not shown in the figure), with the pressure fields and associated fluid pressures shown in a 13 m / s wind.

[0091] [Figure 12E]FIG. 12E is a rear view showing the downstream surface of the blade without the benefit of a deflector, with the pressure fields and associated fluid pressures shown in a 13 m / s wind.

[0092] [Figure 12F] FIG. 12F is a rear view showing the downstream surface of the blade of a deflector / blade assembly including a deflector (although the deflector is not shown in the figure), with the pressure areas and associated fluid pressures shown in a 13 m / s wind.

[0093] [Figure 12G] FIG. 12G is an enlarged side isometric view of cross section "12G" of the blade of FIGS. 12C and 12E showing the surface pressures on the pressure (upstream) and suction (downstream) surfaces of the cross section.

[0094] [Figure 12H] FIG. 12H is an enlarged side isometric view of section "12H" of the blade of FIGS. 12D and 12F showing the surface pressure on the pressure and suction surfaces of the section (deflectors not shown in the figure).

[0095] [Figure 13A] FIG. 13A is a profile diagram of a deflector / blade assembly showing the angles of attack of two deflector profiles relative to a blade profile, with one deflector profile closer to the oncoming fluid flow than the blade profile on the pressure side of the blade and one deflector profile farther from the oncoming fluid flow than the blade profile on the suction side of the blade.

[0096] [Figure 13B]FIG. 13B is a profile diagram of a deflector / blade assembly showing (i) the angles of attack of two deflector profiles relative to a blade profile where one deflector profile is closer to the oncoming fluid flow than the blade profile on the pressure side of the blade and one 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 maintaining the deflector angles of attack but moving both deflector profiles closer to the oncoming fluid flow than shown in FIG. 13A.

[0097] [Figure 13C] 13C is a cutaway front view of the deflector / blade assembly excluding any structure connecting the deflector to the blade and highlighting the skew of the chordwise gap between the deflector leading edges at the tip and hub ends relative to the blade trailing edges. To improve clarity of the chordwise gap, this view is not drawn to scale.

[0098] [Figure 13D] 13D is a rear isometric view of the deflector / blade assembly excluding any structure connecting the deflector to the blade and highlighting the horizontal skew of the gap between the deflector leading edge at the tip and hub end relative to the blade trailing edge. To improve clarity of the horizontal skew, this view is not drawn to scale.

[0099] [Figure 13E] FIG. 13E is a profile view of the deflector / blade assembly showing the deflector located on the suction side of the blade.

[0100] [Figure 14A] FIG. 14A is a front view of a partial span deflector and blade assembly along with an embodiment of a fixed connector assembly for retrofitting the partial span deflector to the blade.

[0101] [Figure 14B]FIG. 14B is a cutaway close-up view of the front of the partial span deflector and blade assembly along with an embodiment of a fixed connector assembly for retrofitting the partial span deflector to the blade.

[0102] [Figure 14C] FIG. 14C is a cutaway side cross-sectional view of a partial span deflector and blade assembly along with an embodiment of a fixed connector assembly for retrofitting the partial span deflector to the blade.

[0103] [Figure 14D] FIG. 14D is a cutaway side exploded isometric view of an embodiment of a partial span deflector-blade connector assembly, with the blade and deflector not shown.

[0104] [Figure 14E] FIG. 14E is a cutaway side isometric view of an embodiment of a partial span deflector-blade connector assembly, with the blade and deflector not shown.

[0105] [Figure 15] FIG. 15 is a front isometric view of a non-uniform thickness deflector, excluding any structure connecting the deflector to the blades, with enlarged and detailed (i) cross-sectional side views of the tip and center sections and (ii) a side view of the hub end.

[0106] [Figure 16A] FIG. 16A is a front view of an embodiment of a deflector / blade assembly with a curved deflector tip end.

[0107] [Figure 16B] FIG. 16B is a front cutaway close-up view of an embodiment of a deflector / blade assembly with a curved deflector tip end.

[0108] [Figure 17A]FIG. 17A is a front view of an embodiment of a deflector that includes an arcuate trailing edge near its distal end superimposed over a deflector that does not have an arcuate trailing edge near its distal end.

[0109] [Figure 17B] FIG. 17B is an end view of an enlarged detailed tip of an arcuate trailing edge superimposed over a deflector without the arcuate trailing edge.

[0110] [Figure 17C] FIG. 17C is an enlarged, detailed cross-sectional view of the arcuate trailing edge at line CC of FIG. 17A superimposed over a deflector without the arcuate trailing edge.

[0111] [Figure 18A] FIG. 18A is a front view of an embodiment of a deflector with a wall protruding from the upstream surface of the deflector.

[0112] [Figure 18B] FIG. 18B is a cutaway, enlarged, isometric view of the deflector with a wall protruding from the upstream surface.

[0113] [Figure 19A] FIG. 19A is a rear view of an embodiment of a multi-section deflector / blade assembly with a fixedly coupled connector assembly, with an enlarged, cutaway, detailed rear view of the connection between the two deflector sections and an enlarged, cutaway, detailed side cross-sectional view of the connection between the two deflector sections.

[0114] [Figure 19B] FIG. 19B is a side isometric view of a two-part deflector-blade connector assembly with cutaway enlargements: (i) a detailed isometric view of the connection between the connector sections, and (ii) a detailed isometric exploded view of the connection between the two connector sections.

[0115] [Figure 20A]FIG. 20A is a rear isometric view of an embodiment of a deflector / blade assembly with a variable angle connector assembly.

[0116] [Figure 20B] 20B is a side view of the deflector chord depicting four ranges of deflector angle of attack at five positions relative to the rotor rotation plane, starting with the deflector leading edge closest to the oncoming fluid flow to the deflector leading edge furthest from the oncoming fluid flow. To improve clarity of articulation, this view is not drawn to scale and the deflector profile is not shown.

[0117] [Figure 20C] FIG. 20C is a cutaway rear isometric view of the deflector / blade assembly with the variable angle connector assembly, with the deflector in a fully retracted position (its rear edge furthest from the oncoming fluid flow), with the cutaway section revealing the motor drive components and the deflector-connector assembly connection.

[0118] [Figure 20D] FIG. 20D is a cutaway rear isometric view of the deflector / blade assembly with the variable angle connector assembly, with the deflector in a fully extended position (its rear edge furthest from the oncoming fluid flow), with the broken cross section revealing the motor drive components and the deflector-connector assembly connection.

[0119] [Figure 20E] 20E is a cutaway rear view of the motor and associated main drive train components of the variable angle connector assembly located within the blade, which is not shown to reduce the complexity of the illustration.

[0120] [Figure 20F] FIG. 20F is an exploded isometric view of the deflector end of the flexible rod assembly cut away, with the cutaway section revealing (i) a cutaway view of the deflector and (ii) internal details of the guide tube.

[0121] [Figure 20G] FIG. 20G is an exploded isometric view of a flexible rod assembly used in conjunction with a variable angle connector assembly, with cutaway and cross-sectional views of the internal details of the guide tube.

[0122] [Figure 20H] FIG. 20H is a cutaway, enlarged, rear isometric view of a portion of the deflector variable angle connector assembly located within the blade, with the cutaway section revealing a cross-sectional view of the structural and guide tube components.

[0123] [Figure 20I] FIG. 20I is an enlarged isometric view of a guide tube assembly with a mating male keyed assembly.

[0124] [Figure 21A] FIG. 21A is a side profile schematic showing ten points along the deflector chord illustrating exemplary X and Y dimensions for one embodiment of a deflector.

[0125] [Figure 21B] FIG. 21B is a table of dimensions corresponding to FIG. 21A.

[0126] [Figure 21C] FIG. 21C is a side view of the deflector with a section line corresponding to FIG. 21B.

[0127] [Figure 21D] FIG. 21D is a table of deflector spanwise dimensions, measured from the deflector tip, corresponding to the tables of FIGS. 21B and 21C.

[0128] [Figure 22A] FIG. 22A is an isometric view of the deflector and blade geometry coordinate system corresponding to the dimensional data table of FIG. 22B.

[0129] [Figure 22B]FIG. 22B is a dimensional data table illustrating an example positioning and angling of the deflector relative to the blade and including data corresponding to a simulated deflector / blade assembly described herein. DETAILED DESCRIPTION OF THE INVENTION

[0130] Detailed Description Unless otherwise defined, all technical terms, notation, and other scientific or technical terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this disclosure belongs. To the extent that a definition set forth in this section contradicts or otherwise conflicts with a definition set forth in any patent, application, published application, or other publication incorporated herein by reference, the definition set forth in this section shall take precedence over the definition incorporated herein by reference.

[0131] References herein to "one embodiment," "an embodiment," "a further embodiment," "an exemplary embodiment," "some aspects," "a further aspect," "aspects," and the like indicate that the described embodiment may include a particular feature, structure, or characteristic, but not all embodiments encompassed by the present disclosure necessarily include the particular feature, structure, or characteristic. Also, such phrases do not necessarily refer to the same embodiment. Furthermore, when a particular feature, structure, or characteristic is described in connection with one embodiment, such feature, structure, or characteristic is also described in connection with other embodiments, whether or not explicitly described.

[0132] Unless otherwise indicated or the context suggests otherwise, as used herein, "a" or "an" means "at least one" or "one or more."

[0133] This description may use various terms describing relative spatial arrangement and / or orientation or direction when describing the position and / or orientation of a component, device, location, feature, or portion thereof, or the direction of movement, force, or other dynamic action. Unless specifically stated or otherwise dictated by the context of the description, such terms, including but not limited to top, bottom, above, below, under, above, underneath, left, right, in front of, behind, directly below, adjacent to, adjacent to, between, horizontal, vertical, diagonal, longitudinal, lateral, radial, axial, clockwise, counterclockwise, etc., are used for convenience when referring to such component, device, location, feature, or portion thereof, or movement, force, or other dynamic action, as depicted in the drawings, and are not intended to be limiting.

[0134] Unless otherwise indicated or the context suggests otherwise, terms used herein to describe the physical and / or spatial relationship between a first component, structure, or portion thereof, and a second component, structure, or portion thereof, such as attached, connected, fastened, joined, coupled, coupled, or similar terms or variations of such terms, are intended to encompass both a direct relationship in which the first component, structure, or portion thereof is in direct contact with the second component, structure, or portion thereof, or the presence of one or more intervening components, structures, or portions thereof between the first component, structure, or portion thereof and the second component, structure, or portion thereof.

[0135] Additionally, unless otherwise stated, any specific dimensions referred to in this description merely represent example implementations of devices embodying aspects of the present disclosure and are not intended to be limiting.

[0136] To the extent used herein, the terms "first" and "second" preceding the name of an element (e.g., a component, device, location, feature, or portion thereof, or direction of movement, force, or other dynamic action) are used for distinguishing purposes to distinguish between similar elements and are not intended to necessarily imply an order or to exclude the inclusion of additional similar elements. Furthermore, the use of the term "first" preceding the name of an element (e.g., a component, device, location, feature, or portion thereof, or direction of movement, force, or other dynamic action) does not necessarily imply or require that additional such elements, e.g., a "second," "third," etc., are present.

[0137] As used herein, the term "fixedly connected," as used to refer to a 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 and second items.

[0138] As used herein, the term "operably coupled," as used to refer to a physical arrangement between two or more items, means that one item is attached to or otherwise coupled to another item via structures and / or mechanisms that allow for and / or effect relative movement between the first and second items such that the position and / or orientation of the first item relative to the second item can be selectively (including automatically) altered.

[0139] As used herein, the terms "optional" and "optionally" or "may" (e.g., as in the phrases "may include," "may comprise," "may produce," "may provide," or similar phrases) mean that a subsequently described component, structure, element, event, circumstance, characteristic, property, etc. may or may not be included or occur, and that the description includes instances in which the component, structure, element, event, circumstance, characteristic, property, etc. is included or occurs as well as instances in which it is not included or occurs.

[0140] As used herein, the terms "substantially" and "substantially" refer to a considerable degree or extent. For example, when used in conjunction with an event, circumstance, characteristic, or property, the term can refer to instances in which the event, circumstance, characteristic, or property occurs exactly as described, as well as instances in which the event, circumstance, characteristic, or property occurs to an approximation, taking into account, for example, typical tolerance levels or variability of the embodiments described herein.

[0141] As used herein, the term "airfoil section" means a portion of a blade having a shape that generates a pressure differential (lift) between opposing surfaces due to the relative movement of air over the airfoil section.

[0142] As used herein, "apparent velocity" or "apparent flow" (or alternatively, "effective velocity" or "effective flow") is the fluid flow, e.g., air flow, water flow, liquid flow, or gas flow, to which a rotor blade is exposed, and is the vector sum of the oncoming fluid flow and the rotational flow induced by the rotation of the blade about the rotor axis of rotation.

[0143] As used herein, the term "bearing" refers to a component used to support and / or guide a rotating, oscillating, articulating, or sliding shaft, pivot, wheel, or assembly. Whether a bearing is described or shown, it may take a number of forms, including, but not limited to, sealed, non-sealed, roller, ball, angular, needle, and thrust. However, unless specifically stated otherwise, when such a term is used, it indicates that the actual connection or coupling may take a variety of forms that will be readily apparent to one skilled in the art.

[0144] As used herein, the terms "blade," "rotor blade," and "turbine blade" refer to any embodiment of a blade used on a fluid-powered turbine, including, but not limited to, wind turbines and hydroturbines.

[0145] As used herein, the term "blade angle of attack" refers to the angle of the blade chord or blade chord line relative to the rotor plane of rotation at a given point along the blade span.

[0146] As used herein, the term "bushing" refers to a component used to serve as a guide for a component that rotates, slides, articulates, or otherwise moves therein, and may take a number of forms, including, but not limited to, self-lubricating, metal polymer composite, bronze-coated, filament-wound, and injection molded. However, unless specifically stated otherwise, when such a term is used, it indicates that the actual connection or coupling may, in certain instances, take a variety of forms that will be readily apparent to one of ordinary skill in the art.

[0147] As used herein, the term "CAD model" refers to a virtual model of a part or collection of parts, including, but not limited to, a rotor, blade, deflector, or blade / deflector assembly, created using computer-aided design (CAD).

[0148] As used herein, the term "chord line" refers to a line that passes through the leading and trailing edges of a deflector or blade and is collinear with and may extend beyond the chord. The term may also be used as a reference position relative to the rotor rotation plane at a given point along the blade or deflector span when describing the blade or deflector angle of attack.

[0149] As used herein, the term "chord" refers to the distance, sometimes shown as a line and / or used as a reference position relative to the rotor rotation plane at a given point along the blade or deflector span, between the trailing edge and the point where the chord intersects the leading edge. The term may be used when describing such a distance or the angle of attack of a deflector or blade.

[0150] As used herein, the terms "computer," "computer-controlled," and similar 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 configured to effect computational and / or control steps by receiving one or more input values, executing one or more algorithms stored on a non-transitory machine-readable medium (e.g., software) that provide 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, e.g., regarding the status of an instrument or a process being performed thereby, or such output may comprise input to other process and / or control algorithms and / or computers. Data input components comprise elements by which data is input for use by control and computing hardware components. Such data inputs may include signals generated by computers, sensors, or scanning devices such as position sensors, speed sensors, accelerometers, environmental (e.g., temperature and barometric pressure) sensors, motor encoders, barcode or RFID scanning devices, pressure sensors, as well as manual input elements such as keyboards, stylus-based input devices, touch screens, microphones, switches, manually operated scanning devices, etc. Data inputs may also include data read from memory. Data output components may include hard drives or other storage media, data transmission components (e.g., LAN, WiFi), monitors, printers, indicator lights, or audible signaling elements (e.g., chimes, buzzers, horns, bells, etc.). The computer may include one or more uninterruptible power supplies.

[0151] As used herein, the term "connector assembly" refers to the structure that connects the deflector to the turbine blade.

[0152] As used herein, the term "concave" refers to a portion of a surface that is concave when viewed as part of a profile.

[0153] As used herein, the term "convex" refers to a portion of a surface that is convex when viewed as part of a profile.

[0154] As used herein, the term "deflector" 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 so as to affect the fluid flow impinging on the associated blade regardless of the orientation of the rotor's longitudinal axis (axis of rotation) or the direction of rotor rotation.

[0155] As used herein, the term "deflector angle of attack" refers to the angle of the deflector chord or deflector chord line relative to the rotor plane of rotation at a given point along the deflector span.

[0156] As used herein, the term "deflector / blade assembly" or "turbine blade assembly" refers to any collection of rotor or turbine blades and one or more deflectors, including all embodiments as described herein.

[0157] As used herein, the term "edge" means any intersection where the pressure and suction sides of a deflector meet, including, but not limited to, arcs, decreasing and increasing radii, and decreasing and increasing curvatures.

[0158] As used herein, the term "flexible shaft" refers to a component configured to transmit force or rotational motion through a non-linear path that is capable of withstanding axial compressive or tensile loads in the longitudinal direction and flexibly adapts across its cross section in the transverse direction. Unless specifically stated otherwise, when such a term is used, it indicates that the device may take a variety of forms. The structure may include a core composed of wires, strands, or fibers wound in layers in opposing directions around a central wire or wire-like structure, and a casing composed of one or more layers of similar or dissimilar materials, including metals, composites, fabrics, plastics, and rubbers. The layers may include a reinforcing braid. Some flexible shafts may have all of these components, while others may have one or more. In certain cases, suitable structures will be readily apparent to those skilled in the art.

[0159] As used herein, the term "flow simulation" refers to a computational fluid dynamics (CFD) simulation, also referred to herein as a "flow analysis."

[0160] As used herein, the term "flow straightener" in relation to fluid flow refers to a device that reduces swirl and asymmetry in the fluid flow.

[0161] As used herein, the term "total torque" refers to the combined positive and / or negative torque from all deflector and blade surfaces within the deflector / blade assembly on the turbine of which the deflector / blade assembly is a part, and is always a positive number in the desired direction of rotation about the hub axis.

[0162] As used herein, the term "hub end" refers to the portion of a blade and / or deflector nearest the hub of the associated rotor as defined herein.

[0163] As used herein, the term "hydrofoil section" means a portion of a blade having a shape that generates a pressure differential (lift) between opposing surfaces due to the relative movement of water or other liquid against the hydrofoil section.

[0164] As used herein, the term "hydroturbine," also referred to as a "water turbine," refers to a system intended to convert kinetic fluid energy from a moving liquid or mixture of liquids, including but not limited to water, into mechanical energy.

[0165] As used herein, the term "motor" refers to a machine that converts electricity or pressure, including but not limited to hydraulic and pneumatic pressure, into mechanical energy, e.g., rotational energy.

[0166] As used herein, the term "negative torque" refers to a torque component acting on the deflector and / or blade surface in the opposite direction of the desired rotation about the rotor axis of rotation.

[0167] As used herein, the term "positive torque" refers to a torque component acting on the deflector and / or blade surface in the direction of desired rotation about the rotor axis of rotation.

[0168] As used herein, the term "profile" when referring to a blade or deflector refers to a chordwise slice (i.e., from leading edge to trailing edge) of the blade or deflector showing the shape of the blade or deflector between the opposing upstream (pressure) and downstream (suction) surfaces.

[0169] As used herein, the term "pressure side" means the surface or area adjacent to the surface of a deflector or blade that is closer to the oncoming fluid flow, also referred to as the "upstream," "windward," or "upwind" side.

[0170] As used herein, the term "pressure" in reference to fluid pressure is relative to atmospheric pressure. It is expressed as a positive number when above atmospheric pressure and a negative number when below atmospheric pressure. Positive pressure values ​​are commonly referred to as pressure or positive pressure, and negative pressure values ​​are commonly referred to as suction.

[0171] As used herein, the term "pressure surface" means the surface of a deflector or blade that is closer to the oncoming fluid flow, also referred to as the "upstream," "windward," or "upwind" side.

[0172] As used herein, the term "cambered camber line" or "cambered mean camber line" refers to a mean camber line that has a reversal of curvature from its first direction that results in it curving upward toward the chord at the deflector trailing edge. The center of curvature of the cambered mean camber line is located on the downstream 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.

[0173] As used herein, the term "right-angle drive" means a mechanism with a gear train that can transmit input torque and rotational motion laterally (e.g., 90 degrees). A right-angle drive may be configured with (i) an input shaft that, when powered, rotates the output shaft through a 90° angle, and (ii) an optional additional output shaft that is collinear with, rotates, and is powered by the input shaft (commonly known as a three-way right-angle drive or three-way right-angle gearbox).

[0174] As used herein, the term "rotational flow" means fluid flow induced by the rotation of the blades about the rotor axis of rotation and which is a component of the apparent velocity.

[0175] As used herein, the term "rotor" means a collection of wind or hydro blades.

[0176] As used herein, the term "rotor blade" is synonymous with the term "turbine blade" and means a wind or hydro turbine blade that is part of a rotor.

[0177] As used herein, the term "seal" refers to a device or material used to act as a fluid barrier to prevent the exchange of fluids in static, low / high pressure, or vacuum environments. Regardless of how it is indicated, its use can take many forms, including, but not limited to, media / environment physical seals, coatings to 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 such terms are used, they indicate that the actual seal may, in certain instances, take a variety of forms that will be readily apparent to one skilled in the art.

[0178] As used herein, the term "swept volume" means the three-dimensional space through which the deflector or blade travels about the rotor axis of rotation.

[0179] As used herein, the term "suction" in reference to fluid pressure is relative to atmospheric pressure and is expressed as a negative number, also commonly known as negative pressure.

[0180] As used herein, the term "suction side" means the area at or near the surface of a deflector or blade that is opposite or generally opposite the pressure side surface and farther from the oncoming flow, also known as the "lee" or "downstream" side.

[0181] As used herein, the term "suction surface" means the surface of a deflector or blade that is opposite or generally opposite the pressure side surface and farther from the oncoming flow, also known as the "downstream" or "lee" side.

[0182] As used herein, the term "tip end" refers to the portion of the blade and / or deflector nearest its respective tip end.

[0183] As used herein, the term "VAC assembly" refers to a variable angle connector assembly that connects the deflector to the turbine blade and allows for changing the orientation of the deflector relative to the turbine blade.

[0184] As used herein, the term "wind turbine" refers to a system intended to convert kinetic fluid energy from a moving gas or gaseous mixture, including, but not limited to, air, into mechanical energy.

[0185] As used herein, the term "working section" refers to a portion of a blade having a shape that generates a pressure differential (lift) between opposing surfaces due to the relative movement of a fluid, e.g., air, water, or other liquid or gas. The working section may be referred to as the airfoil section on a wind turbine blade or the hydrofoil section on a hydroturbine blade.

[0186] All possible combinations of the elements and components described herein or recited in the claims are contemplated and considered part of this disclosure. It should be understood that all combinations of the concepts discussed in more detail below (provided that such concepts are not mutually inconsistent) are contemplated as being part of the subject matter disclosed herein.

[0187] Preferred embodiments will now be described with reference to the accompanying figures, in which like numerals, including those followed by a letter or a hyphen and the letter, e.g., "-A," refer to like elements throughout. Terminology used in the following description, including, but not limited to, the words "upper" and "lower," is not to be construed in any limiting or restrictive manner simply as it is used in conjunction with the detailed description of certain specific embodiments. Furthermore, many components described herein and shown in the drawings and depicted as solid components are so depicted for ease of understanding of the drawings. Notwithstanding the cross-hatching of such components, all such components may be manufactured using conventional (i) assembly techniques whereby a single component is divided into multiple pieces that, when reassembled, may embody the properties of the component described herein and / or shown in the drawings, and (ii) weight-saving methods, including, but not limited to, the design of all such components in multiple subassemblies that may be assembled using conventional assembly techniques into the particular component as shown. At the designer's option, all components may also have internal lattice-like or other non-solid internal designs with reinforced and / or thickened areas where required, for example in areas in contact with bearings or supports and on external wall surfaces, so that such components may appear solid when in fact they are not necessary to achieve their desired functionality.

[0188] Provided herein and shown on the accompanying figures are deflector configurations that may be fixedly coupled and / or operably associated with one or more wind or hydro turbine blades.

[0189] The embodiments disclosed herein allow for multiple configurations of deflector size and shape, including, but not limited to, (i) different aspect ratios (ratio of chordwise width to spanwise length) of the deflector and (ii) locations relative to the pressure and suction sides of the individual blades to which the deflector is fixedly coupled or operably associated. Additionally, the description and drawings are not intended to be limitations regarding the physical shape, size, location of the deflector, or the type of fluid in which the deflector is operating. 1. Prior Art - Wind Turbine Figures 1A-2D

[0190] 1A , a fluid flow turbine 100 is exemplary of embodiments disclosed herein. The fluid flow turbine 100 may comprise a horizontal axis wind turbine (“HAWT”). The fluid flow turbine 100 includes a rotor 110 with a plurality of rotor blades 111 (e.g., three) mounted to and extending radially from a hub 121 that defines a rotor axis or rotor rotation axis 123 (also referred to herein as a hub axis or hub rotation axis) about which the rotor 110 rotates in a direction 5 (counterclockwise in the illustrated embodiment). In alternative embodiments, the rotor 110 includes more or less than three rotor blades 111 and / or rotates clockwise.

[0191] 1B , still referring to FIG. 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 operatively coupled to or defining a rotational axis 123 of the rotor 110, which converts the kinetic energy of an oncoming fluid flow (wind current) 1, via rotor blades 111, into rotational energy that is harnessed in the gearbox 126. The gearbox 126 is rotated by the rotor 110 and may be coupled to a device that converts the rotational energy, such as a generator 128 or a fluid pump (not shown). Note that some wind turbines may use a direct drive generator that is directly coupled to the rotor 110, eliminating the need for the gearbox 126.

[0192] Turbine 100, i.e., rotor 110 and nacelle 138, may be mounted on tower 124, which defines tower axis 125. A wind speed and direction sensor 139 may be mounted on nacelle 138 and connected to a computer (not shown) to monitor wind turbine operation, e.g., to orient rotor 110 perpendicular to the oncoming fluid flow 1 and adjust rotor blades 111.

[0193] 2A and 2B, each rotor blade 111 may include a blade root 158 ​​at its inner end relative to the hub 121 (see FIG. 1A), a connecting structure 157 (e.g., an annular mounting flange) for securing the rotor blade 111 to the hub 121, and a blade tip 151 at its radially outer end relative to the hub 121, defining a span 154 from the blade root 158 ​​to the blade tip 151. The rotor blade 111 may include a root section 160, which may be generally circular, elliptical, oval, or oval in cross-sectional profile at the blade's distal root end 158 as it progresses from the blade root end 158, and a working section of the rotor blade 111, the airfoil section 164, having a leading edge 168 and a trailing edge 174 that generally define an airfoil profile between them, forming a pressure surface (or upstream surface) 178 facing the oncoming fluid flow 1 (see FIG. 1A) and a suction surface (or downstream surface) 182 (see FIG. 2B).

[0194] Each rotor blade 111 also includes a tip section 150 that overlaps a portion of the airfoil section 164, and a leading edge 168 and a blade trailing edge 174 that define a pressure surface 178 and a suction surface 182. Referring to details A, B, and C of FIG. 2A , the pressure surface 178 may include a convex surface 181 on the leading side and a concave surface 180 on the trailing side. The blade 111 may include a transition section 184 where the cross-sectional shape of the rotor blade 111 transitions from the circular, elliptical, or other shape of the blade root 158 ​​and root section 160 to the shape of the airfoil section 164. In alternative circumstances, the transition section is omitted, and the blade 111 includes an abrupt, generally instantaneous, transition between the profile of the root section 160 and the profile of the airfoil section 164.

[0195] The wing 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 with increasing distance of the span from the blade root 158, as shown), or the chord 186 may be constant along some or all of the span 154 within the wing section 164.

[0196] 2C, with still reference to FIG. 2A, the airfoil section 164 may have an aerodynamic profile defined by the pressure surface 178 and the suction surface 182 defining 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 spanwise distance from the hub 121 (see details A, B, and C in FIGS. 1A and 2A). The airfoil chord 186 may be arranged at a blade chord angle (or angle of attack) 194 relative to the plane of rotation 104 of the rotor 110 (see FIG. 1A), and the blade chord angle 194 may also vary with spanwise distance from the hub 121.

[0197] Referring now to FIG. 2C , the blade 111 may have an internal support structure including (i) spars 114 and stiffeners 112 on the pressure side 178, (ii) spars 115 and stiffeners 113 on the suction side 182, and (iii) stiffeners 118 at and near the leading edge 168 (collectively, “blade stiffeners”).

[0198] Blade 111 may also have a U-shaped shear web 116 near the center of blade 111 and a U-shaped shear web 117 near the blade leading edge 168 (collectively, "shear webs"). The stiffeners and shear webs provide additional structural support to blade 111. 1.1 Apparent velocity

[0199] 2D , when the rotor 110 is static, i.e., not rotating, each rotor blade 111 is exposed only to the oncoming fluid flow 1, which impinges on the pressure surface 178 of the blade 111. As the flow passes by the blade trailing edge 174 and the blade leading edge 168, the passage of such a flow causes a pressure drop on the suction side 182. The passing flow, moving in a downwind direction, recirculates and generates a vacuum (i.e., a pressure relatively lower than that on the pressure side 178) in the area adjacent the suction side 182. If the suction on the suction surface 182 is lower between the leading edge 168 and the thickest part of the blade than between the thickest part of the blade 111 and the blade trailing edge 174, a positive rotor torque results.

[0200] As the rotor 110 rotates, each rotor blade 111 is exposed to a flow due to the rotor blade 111's movement in the direction of rotation 5 (see FIG. 1A ) within the rotor plane 104, as well as an oncoming fluid flow 1. The result of the flow due to the direction of rotation 5 and the oncoming fluid flow 1 is an apparent velocity (“AV”) or apparent fluid flow. A portion of the apparent velocity AV flows across the pressure side 178 of the blade 111, and a portion of the apparent velocity AV flows across the suction side 182 of the blade 111. Due to the differential curvature 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 more rapidly across the suction side 182 than across the pressure side 178, thereby creating a pressure difference between the suction side 182 and the pressure side 178, which generates a lift force F acting generally perpendicular to the direction of the apparent velocity AV. L In addition, the flow across the blade 111 results in a drag force F acting in a direction parallel to the apparent velocity AV. D Generates lift F L The component of the positive torque F acts on the blade 111. T+ and produces a drag force F D The component of the negative torque F acts on the blade 111. T- F T- F T+ causes the rotor to rotate. 1.2 Useful Areas Figure 2E-Figure 2F

[0201] 2E and 2F, blade 111 has areas on its pressure surface 178 and suction surface 182 whereby, depending on the curvature of the respective surfaces, both pressure and suction can result in positive or negative torque acting on blade 111. This section describes the geometry of blade 111 and its associated angles of attack that cause positive pressure or negative pressure (suction) to result in a positive torque. These areas are defined herein as "useful areas."

[0202] The beneficial area can have positive or negative pressure that, under theoretically ideal conditions (“ideal conditions”), contributes a positive torque to the blade 111, depending on the blade geometry and angle of attack as described below.

[0203] Pressure surface 178 includes area 10, which under ideal conditions would have (i) a positive pressure located between transition point 9 (corresponding to blade trailing edge 174 in the illustration) and transition point 11, and (ii) a negative pressure (suction) in area 12 located between transition point 11 and transition point 13 (corresponding to leading edge 168 in the illustration).

[0204] Suction surface 182 includes an area that, under ideal conditions, would have (i) negative pressure (suction) in area 14, located between transition point 13 and transition point 15, and (ii) positive pressure in area 16, between transition point 15 and transition point 17 (illustrated as corresponding to blade trailing edge 174). 1.3 Useful Areas - How They Work Figure 2G

[0205] 2G, still referring to FIGS. 2E and 2F, any pressure or suction on blade 111 can be described as a series of forces acting normal (locally perpendicular) to blade pressure surface 178 or suction surface 182. Any force applied to blade 111 can be resolved into an axial component (i.e., in a direction parallel to rotor rotation axis 123 (see FIG. 1A)) and a tangential component (i.e., in a direction perpendicular to rotor rotation axis 123). Axial forces do not directly affect the rotation of blade 111. A tangential component of a force in the intended direction of rotation 5 increases positive torque and is therefore beneficial. A tangential component of a force opposite to the direction of rotation 5 results in negative torque and is therefore detrimental.

[0206] The greater the inclination of the blade pressure surfaces 178 relative to the rotor rotation plane 104, e.g., 178-A, 178-B, and 178-C, and the greater the inclination of the blade suction surfaces 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, since the force is applied normal to the surfaces.

[0207] For example, because the angle of slope 178-A is 30 degrees and exceeds slope 178-B (14 degrees), the same pressure at both slopes will generate a greater force in the rotational direction at slope 178-A than at slope 178-B. Such forces are beneficial if they have a tangential component in the rotational direction 5. Area 10 produces a beneficial torque when the set of forces resulting from the pressures all have a tangential force component in the rotational direction 5.

[0208] Because the tangential component of the force in direction 5 exceeds other locations in the illustrated embodiment, the greatest beneficial forces are experienced at locations where the normal force produces a greater angle of inclination relative to the rotor rotation axis 123 (see FIG. 1A), e.g., 178-A, 178-C, and 182-C. The theoretically ideal pressure and suction locations are as follows: [Table 1] 1.4 Effect of Angle of Attack on Useful Area - Figure 2F and Detail A of Figure 2F

[0209] Referring now to FIG. 2F , as the angle of attack of blade 111 changes, the beneficial area can move along blade chord 186. For example, with a 5-degree angle of attack as shown, blade 111 has beneficial area 12, where suction would ideally occur, and area 10, where pressure would ideally occur. However, as blade trailing edge 174 is adjusted toward oncoming flow 1, e.g., at a 12-degree angle of attack, (i) transition point 9 moves toward oncoming flow 1 and downward toward leading edge 168, thus reducing the area of ​​beneficial area 10, and (ii) a third beneficial pressure surface area 10-A is created, located between transition point 9 and transition point 9-A (see detail A in FIG. 2F ). Ideally, area 10-A would benefit most from suction and, in practice, would benefit from reduced pressure and contribute to positive torque in the desired rotational direction 5 of blade 111. 2. Conventional technology - Hydro turbine Figure 3

[0210] 3, a fluid-flow hydroturbine 300 is illustrative of embodiments disclosed herein. The fluid-flow hydroturbine 300 may comprise a horizontal axis water turbine. The fluid-flow turbine 300 includes a rotor 310 with a plurality (e.g., three) of rotor blades 311 mounted on and extending radially from a hub 321 that defines a rotor axis 323 about which the rotor 310 rotates in direction 5 (counterclockwise in the illustrated embodiment). In alternative embodiments, the rotor 310 includes more or less than three rotor blades 311 and / or rotates clockwise.

[0211] The fluid flow turbine 300 may include rotor drive components such as a gearbox 326 and a generator 328 located within a nacelle 338 operatively coupled to or defining a rotor shaft 323 of the rotor 310, which converts the kinetic energy of the oncoming fluid flow (water flow) 1, via rotor blades 311, into rotational energy that is harnessed in the gearbox 326. 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). Note that some fluid flow turbines may use a direct drive generator that is directly coupled to the rotor 310, eliminating the need for the gearbox 326.

[0212] Turbine 300, i.e., rotor 310 and nacelle 338, may be mounted on tower 324, which defines tower axis 325. Fluid velocity and flow direction sensors 339 may be mounted on nacelle 338 and connected to a computer (not shown) to monitor hydroturbine operation, e.g., to orient rotor 310 perpendicular to the oncoming fluid flow 1 and adjust rotor blades 311.

[0213] 4A and 4B, each rotor blade 311 may include a blade root 358 at its inner end relative to the hub 321 (see FIG. 3A), a connecting structure 357 (e.g., an annular mounting flange) for securing the rotor blade 311 to the hub 321 (see FIG. 3A), and a blade tip 351 at the rotor blade's radially outer end relative to the hub 321, defining a span 354 from the blade root 358 to the blade tip 351. The rotor blade 311 may include a root section 360, which may be generally circular, elliptical, oval, or oval in cross-sectional profile at the blade's distal root end 358 as it progresses from the blade root end 358, and a hydrofoil section 364, which is the working section of the rotor blade 311 and has a leading edge 368 and a trailing edge 374 that generally define a hydrofoil profile between them, forming a pressure surface (or upstream surface) 378 facing the oncoming fluid flow 1 (see FIG. 3) and a suction surface (or downstream surface) 382 (see FIG. 4B).

[0214] Each rotor blade 311 also includes a tip section 350 that overlaps the hydrofoil section 164, and the pressure surface 378 may include a leading convex surface 381 and a trailing concave surface 380. The blade 311 may include a transition section 384 where the cross-sectional shape of the rotor blade 311 transitions from the circular, elliptical, or other shape of the blade root 358 and root section 360 to the shape of the hydrofoil section 364. In alternative circumstances, the transition section is omitted and the blade 311 includes an abrupt, generally instantaneous, transition between the profile of the root section 360 and the profile of the hydrofoil section 364.

[0215] Hydrofoil section 364 is defined by a chord 386 between blade leading edge 368 and blade trailing edge 374. Chord 386 may be variable along the span 354 of blade 311 (e.g., chord decreases with increasing distance of span from blade root 358, as shown), or chord 386 may be constant along the portion of span 354 within hydrofoil section 364.

[0216] The fluid dynamics interact with the blades 311 in a similar manner as described in Section 1.1 above. 3. Deflector Location, Length, and Orientation Relative to Blade - Figures 5A-8

[0217] A deflector / blade assembly (or turbine blade assembly) as described herein includes a rotor blade (of a wind, water, or other fluid flow turbine) with a deflector fixed or otherwise coupled to the associated rotor blade. The deflectors described herein may be configured to cooperate with rotor blades that rotate in either a clockwise or counterclockwise rotation.

[0218] 5-8, deflectors, including but not limited to the partial span deflectors described herein, may be configured with wind turbines 100 (see FIGS. 5 and 6), water turbines 300 (see FIGS. 7 and 8), or other fluid-powered turbines. Deflectors similarly affect fluid flow adjacent to and / or near the deflector / blade assemblies in all fluid types. The interaction between deflectors as described herein and associated rotor blades and their relative impact on rotor performance generally does not depend on the type of fluid, e.g., air, water, liquid, or gas, in which the rotor is operating. Therefore, while the following description will refer to wind turbines, it should be understood that the description is generally equally applicable to other fluid turbines, such as water turbines.

[0219] The deflector 200 or partial span deflector 200-A (see Figures 5 and 6, respectively) of the blade 111 to which the deflector is coupled, when positioned adjacent the pressure side 178 and closer to the oncoming flow than the blade, or adjacent the suction side 182 and farther from the oncoming flow than the blade 111 (see Figures 2A and 2B), causes the fluid pressure to increase on the pressure side 178 of the blade 111 and / or decrease on the suction side 182 of the blade 111 compared to the blade 111 without one or more deflectors in a manner that generates greater overall torque in a rotor having a blade with a deflector compared to a rotor having the same blade but without any deflectors. In this context, a deflector coupled to an associated blade means that the deflector is fixedly coupled to the associated blade (mounted or connected in a manner that precludes relative movement between the deflector and the associated blade) or operably coupled to the associated blade (mounted or otherwise coupled via structures and / or mechanisms that allow and / or effect relative movement between the deflector and the associated blade such that the position and / or orientation of the deflector with respect to the associated blade can be selectively (including automatically) altered).

[0220] 5A and 2A , each deflector 200 is configured to affect the entire airfoil section 164 of the associated blade 111 to which it is coupled (i.e., the deflector 200 extends spanwise across all or substantially all of the airfoil section 164), with each deflector 200 positioned on the pressure side 178 of the associated blade 111 aft of the leading edge 168 of the associated blade relative to the direction of rotation 5. One or more additional deflectors 200 may also be configured on the pressure side 178 or suction side 182 of each blade 111. 3.1 Deflector and Blade Swept Volume

[0221] 5B, in one embodiment, the deflector 200 operates in a separate and distinct swept volume, in an area closer to the oncoming fluid flow 1 than the blade 111 operates. For example, the deflector swept volume 35 is closer to the oncoming flow 1 than the blade swept volume 60.

[0222] A rotor 101 is shown consisting of three deflector / blade assemblies, each consisting of a deflector 200 and a blade 111. In this embodiment, a portion of each deflector 200 is positioned within an outer deflector swept volume 30 bounded by (i) a circumferential travel path 31 of the deflector tip 218, centered about the hub axis of rotation 123 at or near the deflector tip 218, and (ii) an inner circumference 33 located closer to the hub axis of rotation 123.

[0223] The depth (ie, axial extent relative to the hub rotation axis 123 ) 32 of the deflector swept volume includes the deflector chord over its spanwise distance from its tip 218 to its circumference 33 .

[0224] A smaller diameter transition swept volume 40 is shared by a portion of the deflector 200 and a portion of the blade 111, such that the geometry of the deflector 200 begins to transition closer to the blade 111 as the distance of the deflector 200 to the hub rotation axis 123 decreases. The transition swept volume 40 is bounded by an outer circumference 33 and an inner circumference 41.

[0225] The smaller diameter area, common swept volume 50, is completely shared by a portion of deflector 200 and a portion of blade 111. Common swept volume 50 is bounded by its outer circumference 41 and by a circumferential travel path 51 of deflector hub end 214, centered about hub rotation axis 123 at or near deflector hub end 214.

[0226] The deflector 200 and the rotor blades 111 share an entire common swept volume 50, where the distance of the deflector 200 away from the oncoming fluid flow 1 increases as its spanwise distance toward the hub rotation axis 123 decreases. That is, progressing from the tip end 218 to the hub end 214, the distance the deflector 200 is advanced toward the oncoming flow 1 relative to the blades 111 decreases.

[0227] The blade 111 has a separate swept volume 60 bounded by the circumferential path of its tip end 151 about the hub rotation axis 123 (slightly beyond the circumference 31 of the deflector 200) and the inner circumference 33. The blade swept volume depth 65 includes the chord of the blade 111 over its spanwise distance from its tip 218 to the circumference 33.

[0228] Deflector 200 as described herein has forty-eight percent (48%) of its span in its outer swept volume 30, twenty-five percent (25%) of its span in transition swept volume 40, and twenty-seven percent (27%) of its span in common swept volume 50. Hypothetical and physical performance for this embodiment is described in Section 7. 3.2 Partial Span and Hydroturbine Blades

[0229] 6 and still referring to FIG. 2A , each partial span deflector 200-A is configured to affect a portion of the airfoil section 164 of the associated blade 111 to which the partial span deflector 200-A is coupled (i.e., the partial span deflector 200-A extends spanwise across less than all of the airfoil section 164), and each partial span deflector 200-A is positioned on the pressure side 178 of the associated blade 111 aft of the leading edge 168 of the associated blade, relative to the direction of rotation 5. One or more additional partial span deflectors 200-A may also be configured on the pressure side 178 or suction side 182 anywhere along the blade span 154.

[0230] 7 and 4A, each deflector 400 is configured to affect the entire hydrofoil section 364 and tip 351 of the associated blade 300 to which it is coupled (see FIG. 4A) (i.e., the deflector 400 extends spanwise across all or substantially all of the hydrofoil section 364), and each deflector 400 is positioned aft of the leading edge 368 of the pressure side 378 of its associated blade 311, relative to the direction of rotation 5. One or more additional deflectors 400 may also be configured on the pressure side 378 or suction side 382 of each blade 311.

[0231] 8, each partial span deflector 400-A is configured to affect a portion of the hydrofoil section 364 of the associated blade 311 to which the partial span deflector 400-A is coupled (see FIG. 4A) (i.e., the partial span deflector 400-A extends spanwise across less than all of the hydrofoil section 364), and the partial span deflector 400-A is positioned on the pressure side 378 of the associated blade 311 aft of the leading edge 368 of the associated blade, relative to the direction of rotation 5. One or more additional partial span deflectors 400-A may also be configured on the pressure side 378 or suction side 382 of each hydroturbine blade 311 anywhere along the blade span 354.

[0232] Partial span deflectors are designed for retrofitting onto existing turbines located where the fluid flow within which the existing turbine operates is less than that required to reach rated capacity.

[0233] Any deflector type, e.g., 200, 200-B, 201, may be configured as a partial span deflector for turbines operating in any fluid type.

[0234] The deflectors described herein may be fixedly coupled or operably associated with the associated blades as described in Sections 6 and 9.7, respectively. 4. General Shape and Orientation of Deflector Relative to Oncoming Flow - Figures 9A-9B

[0235] 9A, which shows a front isometric view of deflector 200, the deflector is bounded by a leading edge 208, a hub end 214, a trailing edge 212, and a tip end 218. In the illustrated embodiment, the general shape of the periphery of deflector 200 is trapezoidal, with the periphery being defined by leading edge 208, hub end 214, trailing edge 212, and tip end 218. However, in other embodiments, the shape of the periphery may not be generally trapezoidal, and may be, for example, quadrilateral.

[0236] The deflectors 200 have a length defined by a deflector span 223 that extends from the deflector tip end 218 to the deflector hub end 214, and may be greater than, less than, or equal to the blade span 154 (see FIG. 2A ). Each deflector 200 is positioned and oriented relative to its associated blade 111 (see FIG. 5 ) so as to have a pressure surface (or upstream surface) 204 that is impinged by the oncoming fluid flow 1 and a suction surface (or downstream surface) 206 opposite the pressure surface 204.

[0237] Deflector 200 is characterized by chords extending from leading edge 208 to trailing edge 212 at any location along span 223, such as tip end chord 224-A and hub end chord 224-E. Tip end chord 224-A and hub end chord 224-E may differ, including, but not limited to, such that (i) when unequal as shown, the shape of the periphery of pressure surface 204 of deflector 200 is generally trapezoidal, and (ii) when equal, the shape of the periphery of pressure surface 204 of deflector 200 is generally quadrilateral.

[0238] In some embodiments, the spanwise curvature of the leading edge 208 of the deflector 200 follows the curvature of the blade trailing edge 174 (see FIG. 9B). In other embodiments, the leading edge 208 of the deflector 200 may be straight or have a curvature that does not follow the curvature or other geometry of the blade 111.

[0239] The deflector 200 may twist along the span 223, similar to the blade twist, and the twist may (i) be linear or non-linear, and / or (ii) may or may not match the twist of the blade to which the deflector 200 is fixedly coupled or operably associated. Flow analysis indicates that matching the deflector twist with the blade twist will increase blade / deflector assembly performance by increasing the overall torque generated by the blade / deflector assembly in the direction of rotation.

[0240] Still referring to FIG. 9A, and now referring to Detail A-Detail C of FIG. 9A, pressure surface 204 has a trailing concave surface 230 that begins at trailing edge 212 and ends at transition point 236, and a leading convex surface 238 that begins at transition point 236 and ends at leading edge 208.

[0241] Deflector 200, deflector 400 (see FIG. 7), and all deflector embodiments described herein may each be constructed from a single material or a combination of two or more materials (e.g., laminates), including, but not limited to, composites, plastics, or metals, with integral supports, including, but not limited to, structural mounting flanges, 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. 5. Concave and Convex Surfaces - General - Figure 9C - Figure 9D

[0242] 9C and 9D, in the illustrated embodiment, the curvature of the trailing concave surface 230 and the leading convex surface 238 varies uniformly or non-uniformly across the span 223 of the deflector 200 (see FIG. 9A), and the trailing concave surface 230 and the leading convex surface 238 at the tip end (FIG. 9C) may have a greater curvature (smaller radius of curvature) than the trailing concave surface 230 and the leading convex surface 238 at the hub end (FIG. 9D).

[0243] In other embodiments, the trailing concave surface 230 and the leading convex surface 238 may remain constant over at least a portion of the span of the blade and / or may vary non-uniformly (increasing or decreasing curvature) over the span 223 (see FIG. 9A). 5.1 Relationship of Concave and Convex Surfaces to Angle of Attack - Figures 9C-9D

[0244] The trailing concave surface 230 and the leading convex surface 238 may each be characterized at any location along the span 223 (see FIG. 9A) of the deflector 200 by its respective depth, which is the maximum distance from the chord at that span location to the pressure surface 204 within the trailing concave surface 230 or the leading convex surface 238, respectively, and is a function of the curvature (radius of curvature) and arc length (or span) of the concave surface 230 or the convex surface 238.

[0245] The convex surfaces 238 shown in Figures 9C and 9D are exaggerated to more easily show their depth measurements.

[0246] 9C, at the tip end 218 of the deflector 200, the depth of the trailing concave surface 230 is length 234 as measured from the tip end chord 224-A to the pressure surface 204, and the depth of the leading convex surface 238 is length 240 as measured from the tip end chord 224-A to the suction surface 206.

[0247] 9D, at the hub end 214 of the deflector 200, the depth of the trailing concave surface 230 is length 248 as measured from the hub end chord 224-E to the pressure surface 204, and the depth of the leading convex surface 238 is length 257 as measured from the hub end chord 224-E to the suction surface 206. In the embodiment shown, the combination and arrangement of the trailing concave surface 230 and the reversal of curvature that occurs in the leading convex surface 238 results in a recurved camber line 226 across the span 223 of the deflector 200 (see FIG. 9A). The center of curvature of the retorted mean camber line 226 is located on the downstream or suction side of the deflector 200 (i.e., outside the downstream surface 206) for one portion of the mean camber line 226 corresponding to the convex surface 238, and on the upstream (or pressure) side of the deflector (i.e., outside the upstream surface 204) for another portion of the mean camber line 226 corresponding to the concave surface 230. Either the concave surface 230 or the convex surface 238 may not be circular, and either portion may have multiple centers of curvature on the downstream or upstream side of the deflector. Other embodiments may be configured without a lower convex surface and therefore may not have a retorted camber.

[0248] Note that due to concave surface 230 and convex surface 238 (the extent of which may be exaggerated in the drawings to improve visualization of these concepts), at least a portion of the line representing chord 224-A ( FIG. 9C ) and at least a portion of the line representing chord 224-E ( FIG. 9D ) may be located outside of deflector 200 (i.e., outside the space between upstream surface 204 and downstream surface 206). In some embodiments, a majority of deflector chord 224 across span 223 (see FIG. 9A ) is outside of deflector 200. In some embodiments, the amount of deflector chord outside of the deflector profile, which may vary along the span of the deflector, may be 25-80% of chord at the tip end of the deflector, 65-90% of chord at the hub end of the deflector, and may vary continuously, e.g., linearly, from the tip end to the hub end.

[0249] The concave depths 234, 248 and convex depths 240, 257 (i) correspond to curvatures, whereby as the respective depths increase, the corresponding curvatures increase (the radii of curvature decrease), and (ii) may vary between the deflector tip end 218 and the hub end 214 (see FIG. 9A).

[0250] In one embodiment, there is a relationship between (i) the depth of convex surface 230 over the length of span 223 (see FIG. 9A) and (ii) the angle of attack of deflector 200, as described below.

[0251] Flow simulations indicate that in certain embodiments with relative deflector / blade positions as shown in FIG. 9E , a ratio of (i) concave depths 234 and 248 of five to twenty percent (5-20%) in individual chords 224-A through 224-E, (ii) convex depths 240 and 257 of zero to fifteen percent (0-15%) in individual chords 224-A through 224-E, and (iii) an angle of attack of zero to fifteen degrees (the angle of attack equals zero degrees when coplanar with the plane of rotation, with positive degrees increasing as the deflector trailing edge is advanced toward the oncoming flow) increases overall torque, depending on the relationship between the amount of convexity and concavity and the deflector angle of attack relative to the rotor plane of rotation, as further explained below. However, due to the large number of optimization variables and alternative embodiments that can be combined, it is possible that improvements in overall torque may be obtained with an expanded deflector angle of attack range and an expanded upper concavity-to-chord ratio.

[0252] The flow simulations also show that a similar increase in overall torque to the deflector / blade assembly, i.e., increased performance, can be achieved using (i) less concavity on the pressure (upstream) surface of the deflector and a greater angle of attack between the deflector and the blade, and (ii) more concavity on the pressure (upstream) surface of the deflector and a smaller angle of attack between the deflector and the blade. The flow simulations further show that either increased concavity (i.e., greater curvature or greater concavity depth 234, 248) or an increased angle of attack between the deflector and the blade results in increased performance of the deflector / blade assembly.

[0253] The operating range of the lower convex surface 238 is less than the operating range for the upper concave surface 230. The lower convex surface 238 influences the flow passing between the leading edge 208 of the deflector 200 and the blade trailing edge 174 from the blade pressure surface side 178 toward the deflector suction surface side 206, in other words, from the upstream side of the blade 111 to the downstream side of the deflector 200. Flow simulations indicate that the flow passing through the opening between the deflector 200 and the blade 111 is an important variable in balancing the overall torque and the type of torque due to the deflector 200 alone, i.e., positive, negative, or neutral.

[0254] Flow simulations also indicate that varying the concavity / angle of attack ("AoA") relationship can result in the deflector 200 contributing positive or negative torque to the deflector / blade assembly. This is illustrated in the table below, which compares representative blade torque, deflector torque, and overall torque for rotor blades and blade / deflector assemblies without deflectors; for comparison purposes, the torque values ​​are normalized by the torque values ​​obtained for the rotor blades alone. The comparisons are made for three representative deflector configurations: (i) high deflector angle of attack (e.g., 13°-15°) and low concavity (e.g., 5%-7% of chord); (ii) medium deflector angle of attack (e.g., 6°-12°) and medium concavity (e.g., 8%-12% of chord); and (iii) low deflector angle of attack (e.g., 0°-5°) and high concavity (e.g., 13%-20% of chord). [Table 2]

[0255] As illustrated in the table above, in this embodiment, providing the angle of attack and concavity depth to chord ratio are as described above, adding a deflector increases the blade torque contribution to the overall torque. Additionally, as the angle of attack changes from high to low and the concavity of the deflector changes from low to high, the blade torque contribution to the overall torque decreases, but the deflector torque contribution to the overall torque increases. In other words, a deflector configuration that results in a low or even negative torque contribution from the deflector results in a higher torque contribution from the blade, thereby offsetting the low or negative deflector torque contribution and providing increased overall torque compared to a blade without a deflector.

[0256] 9C and 9D , the deflector 200 has a deflector thickness 207 between the upstream surface 204 and the downstream surface 206 that can be constant from the deflector leading edge 208 to the 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 deflector thickness), and in other embodiments, the surfaces 204 and 206 are not parallel. When the upstream surface 204 and the downstream surface 206 are curved and parallel, the trailing concave surface 230 on the upstream surface 204 has a corresponding trailing convex surface on the downstream surface 206, and the leading convex surface 238 on the upstream surface 204 has a corresponding leading concave surface on the downstream surface 206. In various embodiments, such as those shown in Figures 9C and 9D, when the thickness of the deflector 200 is relatively small relative to the chord (e.g., tip end chord 224-A and hub end 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., the chord extends into the trailing concave surface 230 and / or the leading convex surface 238. 5.2 Deflector / Blade Assembly Chord Detail - Figures 9E-9J

[0257] 9E, there is shown a top view of an exemplary embodiment of a blade / deflector assembly including blade 111 and deflector 200, showing pressure surface 178 of blade 111 and pressure surface 204 of deflector 200. Details A, B, C, D, and E are transverse profile views of the blade / deflector assembly at cross sections AA, BB, CC, DD, and EE, respectively.

[0258] The angles of blade chords 186-A to 186-E (relative to rotor plane of rotation 104 (see FIG. 1A)) may vary along blade span 154 (see FIG. 2A), as further described below.

[0259] The angles of the deflector chords 224-A to 224-E (relative to the rotor plane of rotation 104 (see FIG. 1A)) may vary along the deflector span 223 (see FIG. 9A), as further described below.

[0260] Figure 9F is an enlarged view of detail A of Figure 9E, showing the tip end profile of the blade / deflector assembly. The profile of blade 111 in Figure 9F has a chord line 196 extending from the blade leading edge 168 through the blade trailing edge 174, and a mean camber line 188 representing a line equidistant from the pressure surface 178 and the suction surface 182. The profile of deflector 200 in Figure 9F has a chord line 258 extending from the leading edge 208 through the trailing edge 212, and the profile of deflector 200 includes a trailing concave surface 230.

[0261] The profile of blade 111 in FIG. 9F is oriented at blade angle of attack 194-A, and the profile of deflector 200 in FIG. 9F is oriented at deflector angle of attack 259-A.

[0262] Still referring to FIG. 9F, the leading edge 208 of the profile of the deflector 200 is spaced from the trailing blade edge 174 of the profile of the blade 111 by a distance 228-A in a direction towards the oncoming fluid flow 1 (upstream).

[0263] FIG. 9G is an enlarged view of Detail B of FIG. 9E , showing the profile of the blade / deflector 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 FIG. 2A ). The profile of the blade 111 of FIG. 9G has a chord line 196 extending from the leading edge 168 through the blade trailing edge 174 and a mean camber line 188 that represents a line equidistant from the pressure surface 178 and the suction surface 182. The blade chord 186-B of the profile of the blade 111 of FIG. 9G (see Detail B of FIG. 9E ) may be different (e.g., longer) than the blade chord 186-A of the profile of the blade 111 of FIG. 9F (see Detail A of FIG. 9E ). Additionally, the mean camber line 188 of the profile of the blade 111 of FIG. 9G may be different from the mean camber line 188 of the profile of the blade 111 of FIG. 9F .

[0264] The profile of the deflector 200 in Figure 9G has a chord line 258 extending from the leading edge 208 through the trailing edge 212 and includes a trailing concave surface 230. The deflector chord 224-B (see Detail B in Figure 9E) of the profile of the deflector 200 in Figure 9G may be different (e.g., longer) than the deflector chord 224-A (see Detail A in Figure 9E) of the profile of the deflector 200 in Figure 9F. The curvature of the trailing concave surface 230 of the profile of the deflector 200 in Figure 9G may be different from the curvature of the trailing concave surface 230 of the profile of the deflector 200 in Figure 9F.

[0265] The profile of blade 111 in FIG. 9G is oriented at a blade angle of attack 194-B, which may differ from the angle of attack 194-A in FIG. 9F due to blade twist.

[0266] The profile of the deflector 200 in Figure 9G is oriented at a deflector angle of attack 259-B. The angle of attack 259-B of the profile of the deflector 200 in Figure 9G may be different from the angle of attack 259-A of the profile of the deflector 200 in Figure 9F.

[0267] The leading edge 208 of the profile of the deflector 200 in Figure 9G is spaced from the trailing blade edge 174 of the profile of the blade 111 in Figure 9G by a distance 228-B in a direction toward the oncoming fluid flow 1 (upstream). The distance 228-B in Figure 9G may differ from the distance 228-A in Figure 9F due to variations in vertical and / or horizontal skew (discussed below).

[0268] Figure 9H is an enlarged view of Detail C in Figure 9E. The profile of blade 111 in Figure 9H has a chord line 196 extending from leading edge 168 through trailing edge 174 and a mean camber line 188 representing a line equidistant from pressure surface 178 and suction surface 182. Chord 186-C (see Detail C in Figure 9E) of the profile of blade 111 in Figure 9H may be different from (e.g., longer than) blade chords 186-A and 186-B (see Detail A and Detail B in Figure 9E, respectively) of the profiles of blade 111 in Figures 9F and 9G. Additionally, mean camber line 188 of the profile of blade 111 in Figure 9H may be different from mean camber line 188 of the profiles of blade 111 in Figures 9F and 9G.

[0269] The profile of the deflector 200 in Figure 9H has a chord line 258 extending from the leading edge 208 through the trailing edge 212 and includes a trailing concave surface 230. The chord 224-C (see Detail C in Figure 9E) of the profile of the deflector 200 in Figure 9H may be different from (e.g., longer than) the deflector chords 224-A and 224-B (see Detail A and Detail B in Figure 9E), respectively, of the profiles of the deflector 200 in Figures 9F and 9G. The curvature of the trailing concave surface 230 of the profile of the deflector 200 in Figure 9H may be different from the curvature of the trailing concave surface 230 of the profiles of the deflector 200 in Figures 9F and 9G.

[0270] The profile of blade 111 in FIG. 9H is oriented at blade angle of attack 194-C, which may differ from blade angles of attack 194-A and 194-B in FIGS. 9F and 9G due to blade twist.

[0271] The profile of deflector 200 in FIG. 9H is oriented at a deflector angle of attack 259-C, which may differ from the angles of attack 259-A and 259-B of the profiles of deflector 200 in FIGS. 9F and 9G, respectively.

[0272] The leading edge 208 of the profile of the deflector 200 in Figure 9H is spaced from the trailing edge 174 of the profile of the blade 111 in Figure 9H by a distance 228-C in a direction toward the oncoming fluid flow 1 (upstream). The distance 228-C in Figure 9H may differ from the distance 228-A in Figure 9F and the distance 228-B in Figure 9G due to variations in vertical and / or horizontal skew (discussed below).

[0273] Figure 9I is an enlarged view of Detail D in Figure 9E. The profile of blade 111 in Figure 9I has a chord line 196 extending from leading edge 168 through trailing edge 174 and a mean camber line 188 representing a line equidistant from pressure surface 178 and suction surface 182. Blade chord 186-D (see Detail D in Figure 9E) of the profile of blade 111 in Figure 9I may be different (e.g., longer) than blade chords 186-A, 186-B, and 186-C (see Detail A, Detail B, and Detail C in Figure 9E, respectively) of the profiles of blade 111 in Figures 9F, 9G, and 9H. Additionally, mean camber line 188 of the profile of blade 111 in Figure 9I may be different from mean camber line 188 of the profiles of blade 111 in Figures 9F, 9G, and 9H.

[0274] The profile of the deflector 200 in Figure 9I has a chord line 258 extending from the leading edge 208 through the trailing edge 212 and includes a trailing concave surface 230. The deflector chord 224-D (see Detail D in Figure 9E) of the profile of the deflector 200 in Figure 9I may be different from (e.g., longer than) the deflector chords 224-A, 224-B, and 224-C (see Detail A, Detail B, and Detail C in Figure 9E), respectively, of the profiles of the deflectors 200 in Figures 9F, 9G, and 9H. The curvature of the trailing concave surface 230 of the profile of the deflector 200 in Figure 9I may be different from the curvature of the trailing concave surface 230 of the profiles of the deflectors 200 in Figures 9F, 9G, and 9H.

[0275] The profile of blade 111 in FIG. 9I is oriented at blade angle of attack 194-D, which may differ from blade angles of attack 194-A, 194-B, and 194-C in FIGS. 9F, 9G, and 9H due to blade twist.

[0276] The deflector 200 profile of FIG. 9I is oriented at a deflector angle of attack 259-D, which may differ from the angles of attack 259-A, 259-B, and 259-C of the deflector 200 profiles of FIGS. 9F, 9G, and 9H, respectively.

[0277] The leading edge 208 of the profile of the deflector 200 in Figure 9I is spaced from the trailing edge 174 of the profile of the blade 111 in Figure 9I by a distance of 228-D in a direction toward the oncoming fluid flow 1 (upstream). Distance 228-D in Figure 9I may differ from distance 228-A in Figure 9F, distance 228-B in Figure 9G, and distance 228-C in Figure 9H due to variations in vertical and / or horizontal skew (discussed below).

[0278] Figure 9J is an enlarged view of Detail E of Figure 9E , showing the hub end profile of the blade / deflector assembly. The profile of blade 111 in Figure 9J has a chord line 196 extending from leading edge 168 through trailing edge 174 and a mean camber line 188 representing a line equidistant from pressure surface 178 and suction surface 182. Blade chord 186-E of the profile of blade 111 in Figure 9J (see Detail E of Figure 9E ) may be different from (e.g., longer than) blade chords 186-A, 186-B, 186-C, and 186-D of the profiles of blade 111 in Figures 9F, 9G, 9H, and 9I (see Detail A, Detail B, Detail C, and Detail D of Figure 9E , respectively). Additionally, the mean camber line 188 of the profile of the blade 111 in Figure 9J may differ from the mean camber line 188 of the profile of the blade 111 in Figures 9F, 9G, 9H, and 9I.

[0279] The profile of the deflector 200 of Figure 9J has a chord line 258 extending from the leading edge 208 through the trailing edge 212 and includes a trailing concave surface 230. The deflector chord 224-E of the profile of the deflector 200 of Figure 9J (see Detail E of Figure 9E) may be different from (e.g., longer than) the deflector chords 224-A, 224-B, 224-C, and 224-D of the profiles of the deflectors 200 of Figures 9F, 9G, 9H, and 9I (see Detail A, Detail B, Detail C, and Detail D of Figure 9E), respectively. The curvature of the trailing concave surface 230 of the profile of the deflector 200 of Figure 9J may be different from the curvature of the trailing concave surface 230 of the profiles of the deflectors 200 of Figures 9F, 9G, 9H, and 9I.

[0280] The profile of blade 111 in Figure 9J is oriented at a blade angle of attack 194-E, which may differ from angles of attack 194-A, 194-B, 194-C, and 194-D in Figures 9F, 9G, 9H, and 9I due to blade twist.

[0281] The deflector 200 profile of Figure 9J is oriented at a deflector angle of attack 259-E, which may differ from the angles of attack 259-A, 259-B, 259-C, and 259-D of the deflector 200 profiles of Figures 9F, 9G, 9H, and 9I, respectively.

[0282] The leading edge 208 of the profile of the deflector 200 in Figure 9J is spaced from the trailing edge 174 of the profile of the blade 111 in Figure 9J by a distance of 228-E in a direction toward the oncoming fluid flow 1 (upstream). Distance 228-E in Figure 9J may differ from distance 228-A in Figure 9F, distance 228-B in Figure 9G, distance 228-C in Figure 9H, and distance 228-D in Figure 91 due to variations in vertical and / or horizontal skew (discussed below). 6. Fixed Connectors and Associated Structures - Figures 9K-9N

[0283] 9K, an embodiment of a deflector 200 is fixedly coupled to the suction side 182 of the blade 111 via one or more connector assemblies (or connector brackets) 261. As shown in FIG. 9M, in one embodiment, the connector assembly 261 includes a deflector end flange 271 at which the connector assembly 261 attaches to the deflector 200, a blade end flange 272 at which the connector assembly 261 attaches to the rotor blade 111, and a connector tube 270 extending between and connecting the blade end flange 272 and the deflector end flange 271. The flange 272 may have one or more holes 286 for fasteners used to fixedly couple the assembly 261 to a structural member within the blade 111, as described below.

[0284] In one embodiment, as shown in Figures 9K and 9L, the connector assemblies 261 have a longitudinal shape between the rotor blades 111 and the deflector 200 that follows their respective travel paths 275 of rotation 5 about the rotor axis of rotation 123 (see Figure 1A) (i.e., each connector assembly 261 conforms to an arc centered on the rotor axis of rotation 123 (see Figure 1A) and having a radius corresponding to the spanwise position of the connector assembly). In the illustrated embodiment, as shown in Figure 9L, the connector tube 270 is shaped to conform to the travel path 275 between the mating blade end flange 272 and deflector end flange 271 (see Figure 9M). Other embodiments of the deflector connector assembly may have different longitudinal shapes.

[0285] The connector assembly 261 embodies two sets of leading and trailing edges, i.e., one set of leading and trailing edges to minimize drag induced by the oncoming fluid flow and a second set of leading and trailing edges to minimize drag induced by the rotating fluid flow and apparent velocity 6. Both sets of edges are described further below.

[0286] FIG. 9L is a cutaway, enlarged rear view of the deflector / blade assembly showing a portion of a single connector assembly 261 (ie, tube 270) that extends between blade 111 and deflector 200.

[0287] 9L & Detail A and 9M & Detail A, connector assembly 261 includes a rotational flow leading edge 276 and a rotational flow trailing edge 278 that are oriented to align with the rotational flow and can be oriented for any particular RPM at the designer's option. That is, tube 270 extends from deflector 200 and from blade 111 substantially into the apparent velocity fluid flow 6 that passes across downstream surface 206 and downstream surface 182, as shown. Due to the curvature of the outer edge of tube 270 (i.e., the edge farthest from downstream surface 206 and downstream surface 182), apparent velocity fluid flow 6 first contacts portion 276 of the outer edge of tube 270, flows around tube 270, and then flows past portion 278 of the outer edge of tube 270. Leading edge 276 begins at the point nearest the oncoming rotational flow and superficial velocity fluid flow 6 and terminates at the apex 277 of the curvature of tube 270 (see Figures 9M and Detail A in Figure 9L). Rotational flow trailing edge 278 begins at apex 277 and terminates at the point on connector assembly 261 nearest deflector trailing edge 212.

[0288] Still referring to FIG. 9L, and now referring to detail A of FIG. 9M, which is a cross section along line AA of FIG. 9M, a longitudinal cutaway view of connector assembly 261 reveals the elliptical shape of an embodiment of tube 270. Cross section AA of 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 symmetrical about a line bisecting the cross section between leading edge 276 and trailing edge 278. Example shapes may include an ellipse, an ogive, a spherically blunted ogive, or a parabolic shape, among other similar shapes.

[0289] Referring now to Detail A of FIG. 9L, the longitudinal shape of connector assembly 261 follows the arc of rotational travel path 275 from leading edge 276 to trailing edge 278.

[0290] Still referring to FIG. 9M , and now referring to detail B of FIG. 9M , which is a cross-section along line BB of FIG. 9M , tube 270 has a leading edge 273 oriented toward oncoming fluid flow 1 and an opposite trailing edge 274. Tube 270 is oriented relative to blades 111 and deflector 200 such that oncoming fluid flow 1 flows around tube 270 from leading edge 273 to trailing edge 274 when the blade / deflector assembly is in a static, non-rotating state. Cross-section BB of tube 270 may have an aerodynamic shape with tapered ends to leading edge 273 and to trailing edge 274 and may be laterally symmetrical about a line bisecting the cross-section between leading edge 273 and trailing edge 274. Example shapes may include an ellipse, an ogive, a spherically blunted ogive, or a parabolic shape, among other similar shapes.

[0291] Thus, tube 270 defines two sets of leading and trailing edges: leading edge 273 and trailing edge 274 for the oncoming fluid flow impinging on the static blade deflector assembly, and leading edge 276 and trailing edge 278 for the virtual fluid flow impinging on the rotating blade deflector assembly. Leading edge 273, trailing edge 274, leading edge 276, and trailing edge 278 of connector tube 270 (collectively, "connector tube edges") reduce drag, for example, by reducing the drag coefficient; i.e., a tapered edge has a lower drag coefficient than does a square edge. Note that trailing edge 274 encompasses both leading edge 276 and trailing edge 278. The geometry of tube 270 can be modified so that its cross section benefits from lower speeds, whereby the leading and trailing edges 273 and 247 are more tapered, or benefits from higher speeds, whereby the leading and trailing edges 276 and 278 are more tapered.

[0292] 9N, in one embodiment, the leading edge 208 of the deflector 200 is positioned near the blade trailing edge 174. The deflector end flange 271 is connected to the deflector 200 (e.g., by mechanical fasteners (screws, bolts, rivets), adhesives, welding, co-molding, layer-by-layer lamination, or some combination thereof) such that the flange 271 is preferably embedded within the thickness of the deflector 200 between the upstream surface 204 and the downstream surface 206. The blade end flange 272 is fixedly coupled to the U-shaped webs 116 and 117 within the blade 111 via fasteners 287. In another embodiment, the deflector-blade connector may be fixedly coupled to the deflector 200 and / or the blade 111 externally. Stiffeners 114 and 115 are fixedly coupled within and strengthen the blade 111, where they are fixedly coupled to the webs 116 and 117. Webs 116 and 117 and stiffeners 114 and 115 may extend along any length of blade span 154 (see FIG. 2A).

[0293] The connector assembly 261 conforms to the twist of the deflector / blade assembly and the concave and convex surfaces of the deflector 200, and thus (i) the twist and / or (ii) the length or angle of the connector assembly 261 may vary over the deflector span 223 (see FIG. 9A). 7. Operating Principle, Flow Simulation Results, and Physical Test Results

[0294] The units of pressure in the plots referenced in this section are expressed in pascals (Pa).

[0295] The deflector 200 increases and decreases pressure and / or velocity at desired locations on the blade 111 (see FIGS. 2A and 2B ), resulting in a positive torque increase on the blade 111 with the benefit of the deflector 200 compared to a similar blade 111 without the benefit of the deflector 200. As a result, the blade 111 benefiting from the deflector 200 has a higher overall torque at a given fluid velocity than a similar blade operating under the same conditions without the deflector; for example, a blade with a deflector starting in an 8 mph wind speed will perform similarly to a similar blade without the deflector starting in an 11 mph wind speed.

[0296] The figures, including profile and isometric views of the blades and deflector / blade assemblies referenced in this section and the plots contained within the referenced figures, are as obtained from flow simulations and correlate with performance data observed during physical testing of scaled physical models. The CAD model of the rotor used in this section is 93 meters in diameter. The pressures and suctions recorded in all profile and isometric views in this section were measured at a distance of 41.66 meters from the rotor axis of rotation 123 (see Figure 1). 7.1 Fluid Flow and Pressure Prior to Rotation - Figures 10A-10F

[0297] Figure 10A is a cross-sectional side view of a static, non-rotating blade 111 without deflector 200, showing the flow trajectory around blade 111. Figure 10B is a cross-sectional side view of a static, non-rotating deflector / blade assembly including blade 111 and associated deflector 200, showing the flow trajectory around the deflector / blade assembly. Because the velocity of fluid flow 1 in Figures 10A and 10B is very low (e.g., 2.0 m / s), blade 111 has not begun to rotate due to mechanical resistance, for example, due to generator 128 (see Figure 1B) and / or due to overcoming the inertia of rotor 110 (see Figure 1A).

[0298] 10A , fluid flow 1 impinging on the pressure surface 178 of blade 111 exhibits a pressure-side transition point 2-A at a distance 16-A from the blade trailing edge 174. Transition point 2-A is where the oncoming fluid flow 1 separates, with (i) a portion of fluid flow 3-A being pushed toward and accelerating around (above) the blade trailing edge 174 of blade 111, and (ii) a portion of fluid flow 4-A being pushed toward and accelerating around (below) the leading edge 168 of blade 111. Fluid flow 4-A moving upwind past the leading edge 168 creates low pressure on the suction side 182 and a desirable positive torque 7-A. Fluid flow 3-A moving upwind across the blade trailing edge 174 creates low pressure on the suction side 182 and an undesirable negative torque 8-A.

[0299] 10B, while still referring to FIG. 10A, the deflector 200 deflects a portion of the oncoming fluid flow 1 that would otherwise pass behind (upward as shown) the blade's trailing edge 174 without impinging on the blade 111, and causes a portion of the oncoming fluid flow 1 that would otherwise impinge on the blade near its trailing edge 174 despite the deflector 200 to flow toward (downward as shown) and around the blade's leading edge 168. The deflected flow results in (i) more fluid volume passing across the blade pressure surface 178, including toward and past the leading edge 168, and consequently across the suction surface 182, resulting in (ii) a desired increase and decrease in pressure on the beneficial area of ​​the pressure surface 178 (see sections 1.2 and 1.3), and (iii) a desired increase and decrease in suction on the beneficial area of ​​the suction surface 182 (see sections 1.2 and 1.3).

[0300] The increased flow volume flowing around the leading edge 168 of the blade 111 creates a desired increase in pressure between transition point 2-B and the blade trailing edge 174 (see area of ​​interest 16 (see FIG. 2G)). The increased volume and pressure (i) moves the pressure side transition point 2-B of the deflector / blade assembly closer to the blade trailing edge 174 compared to transition point 2-A, thus reducing the distance 16-B between transition point 2-B and the blade trailing edge 174 compared to distance 16-A in FIG. 10A; (ii) pushes less fluid flow 3-B of the oncoming fluid flow 1 toward and around the blade trailing edge 174, thus reducing the detrimental suction and negative torque in the beneficial area 16 (see FIG. 2G); and (iii) pushes more fluid flow 4B toward and around the blade leading edge 168 compared to fluid flow 4A in FIG. 10A, thus increasing the suction in the beneficial area 14 (see FIG. 2G) on the blade suction side 178.

[0301] The additional fluid flow 4-B on the pressure side 178 of the blade 111 of the deflector / blade assembly of FIG. 10B is amplified by the oncoming fluid flow 1 and pushed past the blade leading edge 168, thereby reducing the pressure on the suction side 182 of the blade 111 between the transition point 2-B and the blade leading edge 168 compared to a blade 111 without the benefit of the deflector 200 (see FIG. 10A, i.e., compared to a blade having less fluid flow 4-A around the blade leading edge 168).

[0302] As a result, the additional flow volume from deflector 200 results in (i) reduced unfavorable suction and negative torque 8-B compared to 8-A, (ii) increased desirable suction and greater positive torque 7-B compared to 7-A, and (iii) increased overall torque on blade 111 with the benefit of deflector 200 (FIG. 10B) compared to blade 111 without the benefit of deflector 200 (FIG. 10A).

[0303] Figure 10C is a side view of a pressure plot around the blade surface of the blade of Figure 10A, and Figure 10D is a side view of a pressure plot around the blade and deflector surfaces of the deflector / blade assembly of Figure 10B. Referring now to Figures 10C and 10D, the performance improvement seen in pressure is visible when comparing the two pressure plots and is highly significant near the blade trailing edge 174 (see Figures 10C and 10D) on the blade suction side 182, where the minimum pressure of -4.09 Pa (pressure range -4.09 to -1.72 Pa) on the blade 111 without the benefit of the deflector 200 of Figure 10C has dropped by more than 2.5 times to -1.42 Pa in Figure 10D (pressure range -1.42 to -1.37 Pa) in the same area on the suction side of the blade 111 benefiting from the deflector 200. It is important to note that the performance improvement shown in the plots (FIGS. 10C and 10D) occurs near the blade tip end 151 (see detail A in FIG. 9E) where the moment arm is longest, thus contributing to the blade benefiting from the deflector beginning to rotate earlier and at a lower fluid velocity than the blade not benefiting from the deflector.

[0304] The 93-meter CAD model, described above and followed by flow analysis results, was scaled down by a factor of 146.4 and its chord was truncated by three percent (3%) to accommodate 3D printing technology. The physical diameter is 25 inches. Performance was measured using redundant sensors, all with identical results, and recorded using a programmable logic controller. Sample physical test performance data compares scaled model rotors with blades with and without deflectors, with both rotors subjected to the same load (resistance) from 0 to 15.5 m / s. Results from 0 to 2.68 m / s are included in the table below. As demonstrated by the test data, rotor rotation is initiated at a lower wind speed for the rotor with blades with deflectors, and rotor rotation at the same wind speed is higher for the rotor with blades with deflectors. [Table 3]

[0305] 10E and 10F, both of which are enlarged side isometric views of FIGS. 10A and 10B, respectively, showing the surface pressures on the upstream and downstream surfaces of the cross section, with pressure regions displayed on the outside of the upstream surface and on the inside of the downstream surface. Significant performance improvements can be seen across the suction surface 182 of blade 111. For example, the narrow cross-hatched portion of the suction surface of blade 111 benefiting from deflector 200 (see FIG. 10F) has a lower pressure magnitude of −1.37 to 1.32 Pa in beneficial area 16 (see FIG. 10G) than the suction surface of the blade without the benefit of deflector 200, which has a pressure magnitude of −1.67 to 1.62 Pa (see FIG. 10E). This is the area where negative torque is generated, so the lower pressure has a performance benefit. 7.2 Fluid flow and pressure during rotation at 3.5 m / s - Figures 11A-J

[0306] The figures in this section depict flow simulation results from a 93 meter diameter rotor studied at an oncoming fluid flow 1 velocity of 3.5 m / s and rotating at 4.3 RPM in a desired counterclockwise rotation 5 (downward as shown) about the rotor axis of rotation 123 of the rotor 110 (see FIG. 1A). The center of the profile and isometric views shows results obtained at a distance of 41.66 meters from the rotor axis of rotation 123 (see FIG. 1A). At such a distance from the hub axis, the center of the profile and isometric views in this section rotates at a circumferential speed of 18.8 m / s.

[0307] FIG. 11A is a cross-sectional side view of a rotating blade 111 without a deflector, showing apparent velocity flow trajectories around the blade's pressure (upstream) surface 178 and suction (downstream) surface 182. FIG. 11B is a cross-sectional side view of a rotating deflector / blade assembly, including blade 111 and deflector 200, near the blade's tip as described above, showing apparent velocity flow trajectories and representative pressure regions around the deflector / blade assembly's pressure (upstream) surface 178 and suction (downstream) surface 182. While it is expected that the blade in FIG. 11B would rotate faster than the blade in FIG. 11A due to the improved blade pressure conditions caused by the deflector, which physical testing confirms, the flow analysis did not include a feedback loop to determine RPM based on blade pressure. Therefore, for purposes of the flow analysis, RPM was artificially set to the same level for both the blade with and without the deflector. Therefore, it is expected that the performance results observed in the flow analysis and reported herein will in fact be understated for blades with deflectors.

[0308] 11A , fluid flow from superficial velocity 6 separates as it approaches blade leading edge 168, with fluid flow 7-A passing adjacent pressure side 178 of blade 111 and fluid flow 8-A accelerating adjacent suction side 182 of blade 111. The pressure difference between pressure side 178 and suction side 182 and its interaction with the geometry of blade 111 causes blade 111 to rotate in the desired counterclockwise rotation 5.

[0309] 11B, still referring to FIG. 11A, as apparent velocity 6 approaches blade leading edge 168, it separates such that it is different from what it would be without the benefit of deflector 200, with a greater amount of apparent velocity 8-B passing adjacent blade suction side 182. The difference is caused by deflector 200 creating a high pressure area 19 on the upstream side of deflector 200 and a high velocity low pressure area 20 on the downstream side of deflector 200, which counteracts the drag resulting from high pressure area 19, as explained further below.

[0310] The high pressure area 19 (i) increases in size and magnitude due to the oncoming fluid flow 1 impinging on the deflector 200 and which would otherwise not affect the performance of the blade 111 if it were not benefited by the deflector 200, and (ii) significantly increases the pressure (increases in size and magnitude) in the area 21 adjacent to the blade pressure surface 178 in the beneficial area 10 (see FIG. 2G), thereby diverting more apparent velocity fluid flow 6 across the blade suction surface 182, and therefore, compared to the area 8-A in FIG. 11A. , (iii) increases fluid flow 8-B and positive torque on blade suction surface 182, (iv) slows the apparent velocity of fluid flow 7-B as it approaches and passes through blade pressure side 178, and (v) reduces the volume and velocity of fluid flow 7-B adjacent blade concave surface 180 (see also detail AC in FIG. 2A ), which collectively results in a positive torque on pressure surface 178, increasing the overall torque on blade 111 compared to blade 111 without the benefit of deflector 200 in FIG. 11B, which has a negative torque on its pressure surface 178. The negative torque on the pressure surface in FIG. 11B is without the benefit of deflector 200.

[0311] The high pressure area 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 across the suction surface 182 rather than across the pressure surface 178 (which would normally cause additional drag on the pressure surface 178 in the beneficial area 11 (see FIG. 2G)), thereby converting undesirable pressure side 178 drag into desirable suction surface 182 force near the blade leading edge 168, which then benefits performance by increasing positive torque. The high pressure area 21 also causes the apparent velocity fluid flow 6 to accelerate at a higher velocity adjacent the suction surface 182. The increased flow at a higher velocity across the suction surface 182 causes greater suction from the leading edge 182 through the beneficial area 15 (see FIG. 2G) and, consequently, a greater positive torque on the suction side 182 of the blade 111 than would occur on the blade 111 without the benefit of the deflector 200.

[0312] 11C and 11D, performance improvements are illustrated by beneficial pressure variations along the blade span 154 (see FIG. 2A). For example, referring now to FIG. 11C, (i) the pressure on the beneficial area 10 (see FIG. 2G) of the blade pressure side 178 is 100 to 123 Pa on the blade 111 without the benefit of the deflector 200, compared to 100 to 150 Pa on the blade 111 with the benefit of the deflector 200, which covers more than 1.5 times the surface of the beneficial area 10 (see FIG. 2G), and (ii) the suction on the suction side 182 near the leading edge on the blade 111 in the beneficial area 14 (see FIG. 2G) without the benefit of the deflector 200 is -520 to -250 Pa, compared to -1,006 to -250 Pa on the blade 111 with the benefit of the deflector 200 (see FIG. 11D). As a result, both the blade pressure side 178 and suction side 182 generate a larger positive torque due to the deflector 200 .

[0313] 11E and 11F, the benefit of the deflector 200 in a 3.5 m / s wind on the pressure surface 178 is evident along the blade span 154 (see FIG. 2A). For example, the pressure on the trailing edge concave surface 180 is 100-150 Pa over approximately 28 percent (28%) of the span 154 (see FIG. 2A) of the blade 111 without the benefit of the deflector 200 (see FIG. 11E), compared to 100-150 Pa over at least 79 percent (79%) of the span 154 (see FIG. 2A) of the blade 111 with the benefit of the deflector 200 (see FIG. 11F). Also, the higher pressures shown in FIG. 11F are in more beneficial areas on the blade due to their increased tilt angle (see Section 1.2), i.e., areas of the blade geometry where the pressure differential benefits blade (rotor) performance. Deflector 200 (see FIG. 9A) is not shown in the pressure plots shown in FIGS. 11F, 11H, and 11J.

[0314] 11G and 11H, the benefit of the deflector 200 in a 3.5 m / s wind on the suction (downstream) surface 182 occurs along the blade span 154 (see FIG. 2A). For example, the suction on the suction side 182 near the tip and near the leading edge 168 on the blade 111 without the benefit of the deflector 200 is −956 to −300 Pa (see FIG. 11G), compared to −1,865 to −300 on the blade near the tip and near the leading edge with the benefit of the deflector 200 (see FIG. 11H) (i.e., approximately doubling the maximum suction). Also, as can be seen by comparing Figures 11G and 11H, the area over which the pressure on the suction surface is -1,865 to -300 Pa with the deflector (Figure 11H) is more than three times the size of the area over which the pressure on the suction surface is -956 to -300 Pa without the deflector (Figure 11G).

[0315] Referring now to Figures 11I and 11J, both of which are enlarged side isometric views of cross section 11I of Figures 11E and 11G and cross section 11J of Figures 11F and 11G, respectively, with surface pressures shown on the individual pressure and suction surfaces.

[0316] The benefit of the deflector 200 in a 3.5 m / s wind on the upstream and downstream surfaces of a cross section of the blade 111 (see FIG. 11J) is shown on a cross section of the blade 111 at the same wind speed without the benefit of the deflector 200 (see FIG. 11I). For example, on the blade 111 without the benefit of the deflector 200 (see FIG. 11I), the pressure over a large portion of the pressure surface 178 with the wide crosshatch is 50 Pa to 100 Pa in areas with a small tilt angle, and therefore a less beneficial portion of the area 178 (see sections 1.2-1.3), compared to 100 Pa to 150 Pa shown with a larger tilt angle (see sections 1.2-1.3) in the wide crosshatch area and in the overall beneficial area on the pressure surface 178 on the blade 111 with the benefit of the deflector 200 (see FIG. 11J). Also, on the blade 111 without the benefit of the deflector 200 (FIG. 11I), the suction on the suction side 182, shown in the narrow crosshatch, is -710 to -250 Pa, compared to -1,308 to -250 Pa, shown in the narrow crosshatch area and in the larger beneficial area (see sections 1.2-1.3) on the suction surface 182 on the blade 111 with the benefit of the deflector 200 (FIG. 11J). The increased negative pressure on the suction side 182 near the leading edge 168 due to the deflector 200 generates a higher positive torque, further increasing the performance improvement seen on the blade with the benefit of the deflector 200.

[0317] An additional example of performance improvement through a comparison of commonalities on the pressure surface 178 and suction surface 182 on the blade 111 between a blade without the benefit of a deflector and a blade with a deflector is shown in the table below. However, it is important to note that the pressure side 182 of the blade 111 ideally has areas that benefit from pressure and other areas that ideally benefit from suction. Similarly, the suction side 182 of the blade 111 ideally has areas that benefit from suction and other areas that ideally benefit from pressure (see sections 1.2 and 1.3). The chart below includes the desired pressure type, low pressure (suction), or high pressure, for the point being measured. [Table 4]

[0318] Physical test results at 3.5 m / s were as follows: [Table 5]

[0319] The deflector performs similarly, but as explained further below, the improvement becomes even more pronounced as the fluid velocity increases. 7.3 Fluid flow and pressure during rotation at 13 m / s - Figures 12A-H

[0320] The deflector affects the flow similarly while rotating at all fluid velocities. As a result, the discussion in the previous section about how the deflector functions also applies here. Also, as a result of the kinetic fluid energy being proportional to the square of the fluid velocity, deflector performance improves exponentially as velocity increases. Additionally, the flow trajectory and pressure plots are similar when the deflector / blade assembly is rotating, regardless of fluid velocity; however, the pressure, suction, and overall torque performance figures are significantly higher at higher fluid velocities.

[0321] The figures in this section depict flow simulation results from a 93-meter diameter rotor, studied at an oncoming fluid flow velocity of 13 m / s, rotating at 16 RPM in a desired counterclockwise rotation 5 (downward as shown) about the rotor axis of rotation 123 (see FIG. 1A). The center of the profile and isometric views shows results obtained at a distance of 41.66 meters from the rotor axis of rotation 123 (see FIG. 1A). At such a distance from the rotor axis of rotation 123, the center of the profile and isometric views in this section rotates at a circumferential velocity of 69.8 m / s. Again, for purposes of flow analysis, the blades with and without deflectors rotate at the same speed; therefore, physical testing indicates that the results reported herein for the blade / deflector combination are understated.

[0322] 12A and 12B, the oncoming fluid flow 1 is at 13 m / s and the blade 111 is rotating in a desired counterclockwise direction (downward as shown) about the rotor axis of rotation 123 (see FIG. 1A).

[0323] The performance improvement at a distance of 41.66 meters from the hub axis as described in the preceding paragraph is illustrative of the beneficial pressure variation along span 154 (see FIG. 2A). For example, (i) the pressure on the trailing concave surface 180 (see detail A in FIG. 12C) is 1,200 to 1,800 Pa on the blade 111 without the benefit of the deflector 200 (see FIG. 12A) compared to the blade 111 with the benefit of the deflector 200 (see FIG. 12B) where the pressure over a significant portion of the concave surface is 1,800 to 2,400 Pa; (ii) the maximum suction on the suction side 182 near the leading edge on the blade 111 without the benefit of the deflector 200 is −6,739 Pa compared to −13,032 on the blade with the benefit of the deflector (see FIG. 12B); the increased suction on the suction side 182 of the blade in FIG. 12B is over an area that is more than twice the size and is near the blade tip 151 (see FIG. 2A) where the moment arm is greatest, as explained above.

[0324] 12C and 12D, the benefit of the deflector 200 in a 13 m / s wind on the pressure surface 178 is evident along the blade span 154 (see FIG. 2A). For example, the pressure on the trailing edge concave surface 180 is 0 to 1,200 Pa over more than 58 percent of the span 154 (see FIG. 2A) of the blade 111 without the benefit of the deflector 200 (see FIG. 12C), compared to 1,200 to 2,400 Pa over more than 87 percent of the span 154 (see FIG. 2A) of the blade 111 with the benefit of the deflector 200 (see FIG. 12D). Also, the higher pressures shown in FIG. 12D are in more beneficial areas on the blade due to their increased tilt angle (see Section 1.2), i.e., areas of the blade geometry where the pressure differential benefits blade (rotor) performance. Deflector 200 (see FIG. 9A) is not shown in the pressure plots shown in FIGS. 12D, 12F, and 12H.

[0325] 12E and 12F, the benefit of the deflector 200 in a 13 m / s wind on the suction surface 182 is evident along the span 154 (see FIG. 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 to −2,400 Pa (see FIG. 12E), compared to −23,431 to −2,400 on the blade with the benefit of the deflector 200 (see FIG. 12F) (i.e., approximately doubling the suction over an area more than three times the size).

[0326] 12G and 12H, both of which are enlarged side isometric views of cross section 12G of FIGS. 12C and 12E and cross section 12H of FIGS. 12D and 12F, respectively, with surface pressures shown on the individual pressure and suction surfaces. The benefit of the deflector in a 13 m / s wind on the upstream and downstream surfaces of the cross section of blade 111 is evident on the cross section of blade 111 at the same wind speed. For example, (i) on blade 111 without the benefit of deflector 200 (see FIG. 12G), the pressure on the larger portion of pressure surface 178 with the wide crosshatch is 600 Pa to 1,200 Pa, compared to 1,800 Pa to 2,400 Pa shown in the wide crosshatch area on pressure surface 178 on blade 111 with the benefit of deflector 200 (see FIG. 12H), and (ii) on blade 111 without the benefit of deflector 200, the suction on suction side 182 with the narrow crosshatch is -9,382 to -3,000 Pa (FIG. 12G), compared to -17,139 to -3,000 Pa shown in the narrow crosshatch area on suction surface 182 on blade 111 with the benefit of deflector 200 (FIG. 12H).

[0327] Physical test results at 3.5 m / s were as follows: [Table 6]

[0328] In the embodiment shown, the overall torque of the deflector / blade assembly significantly exceeds that of the blade 111 without the benefit of the deflector 200. Regardless of the torque of the blade 111, the additional positive or negative torque due to the deflector 200 can be positive, negative, or neutral, as described in Section 8. 8. Optimization parameters - Figures 13A-13E

[0329] Deflector / blade performance is affected by the interrelationship of numerous deflector parameters, including (i) overall shape and size, (ii) angle of attack, (iii) position relative to the blade, (iv) trailing edge concave length and depth, leading edge convex length and depth, and (v) vertical and horizontal skew (collectively, "optimization parameters"). Alternative deflector embodiment features include, but are not limited to, suction side deflectors, non-uniform thickness deflector profiles (e.g., general airfoil shapes), curved leading edge tips, arced leading edge tips, fluid walls, and number of deflectors (collectively, "alternative embodiment features").

[0330] Flow simulations and the physical testing they performed in each case indicate that the optimization parameters can be adjusted to obtain (i) increased blade performance over a given fluid velocity range and (ii) increased blade performance over a specific fluid velocity, both simultaneously and across the entire operating speed range. Because deflectors change the environment in which the blades operate, and blades for different rotor sizes and manufacturers have different geometries, the optimization parameters may be used to increase performance for specific blade designs to which deflectors can be customized and attached.

[0331] The optimization parameters may also be used when adding one or more of the alternative embodiments to the deflector, such as the arced tip (see Section 9.4) and fluid wall (see Section 9.5). Due to the interrelationship between the deflector and the blade, when any one or more alternative embodiments are added to a given deflector embodiment, the optimization parameters may be used to modify the peak performance of a given blade / deflector assembly, for example, customized for a specific fluid velocity.

[0332] The increase in overall torque can be achieved in a number of ways, with different results based on the combination of optimization parameters. For example, many flow simulations have shown that the greatest overall torque improvement can be achieved when the deflector has a large negative torque. However, as shown in Section 7, a less negative deflector torque, a positive deflector torque, or a neutral deflector torque may be more desirable, at the expense of a smaller, but significant, increase in overall torque.

[0333] In this section, all illustrations of the deflector 200 and related features share the same numerical portion of the part number when the deflector 200 is located on the suction side of the blade, but are appended with "-S." 8.1 Angle of Attack and Position Relative to Fluid Flow - Figures 13A-13B

[0334] To facilitate understanding of the matters described in this section, (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 help present the subject matter. Figures 13A and 13B each show two deflectors, each at the same relative distance above the blade (i.e., aft of the blade relative to the direction of rotation), and each deflector oriented at the same relative angle of attack. Both deflectors in Figure 13A are farther from the oncoming flow 1 than the deflectors shown in Figure 13B.

[0335] 13A and 13B are used to explain details regarding (i) the position of deflector 200 relative to the oncoming flow 1 when its leading edge is closer to the oncoming fluid flow 1 than the blade trailing edge 174, (ii) the distance of the leading edge 208-S of deflector 200-S aft of the blade trailing edge 174, (iii) the ability to have both deflector 200 and deflector 200-S in some embodiments, and (iv) the propensity to advance the deflector toward the oncoming flow while maintaining its angle of attack. The pressure side of the deflector and blade in all figures referenced in this section is located closest to the oncoming flow.

[0336] Referring now to FIG. 13A, an embodiment is shown with a profile of deflector 200 closer to the oncoming fluid flow 1 than the profile of blade 111 (i.e., deflector 200 is upstream of blade 111, so that fluid flow 1 hits deflector 200 before it hits blade 111), and a second deflector profile 200-S farther from the oncoming fluid flow 1 than blade profile 111 (i.e., deflector 200-S is downstream of blade 111, so that fluid flow 1 hits blade 111 before it hits deflector 200-S), as further described in Section 8.4.

[0337] The deflector angle of attack is shown as (i) positive degrees 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) negative degrees 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 deflector 200 and the deflector 200-S can be positioned or configured with their respective angle of attack positions at either positive or negative degree angles.

[0338] Deflector profile 200 has a chord line 258 at a distance 228 into the fluid flow 1 from 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 and is shown at an angle of attack 259-F of 9 degrees. A second deflector profile 200-S has a chord line 258-S at a distance 229-S downstream from 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.

[0339] Still referring to FIG. 13A, and now referring to FIG. 13B, there is shown an embodiment similar to the embodiment shown in FIG. 13A with (i) a deflector 200 with its chord line 258 closer to the oncoming fluid flow 1 than the profile of the chord 186 of the blade 111, and (ii) a profile of a second deflector profile 200-S with its chord line 258-S farther from the oncoming fluid flow 1 than the chord 186 of the blade 111.

[0340] However, the deflectors 200 and 200-S and their respective chord lines 258 and 258-S in Figure 13B are closer to the oncoming fluid flow 1 than those configured in Figure 13A compared to the deflectors 200 and 200-S shown in Figure 13A. In all cases in Figures 13A and 13B, the respective deflector angles of attack for each deflector chord line 258 and 258-S remain constant, e.g., 9° and -11°, respectively. The respective angles of attack remain constant in these examples due to the different respective chord plane distances 228-S and 229-S in Figure 13B from the distances 228 and 229 in Figure 13A.

[0341] As deflector chord line 258 and / or 258-S are advanced toward the oncoming fluid flow 1, angles of attack 259-F and 260-A may be maintained as shown, or may also be modified. If the angle of attack is maintained while advancing chord line 258 toward the oncoming fluid flow 1, distance 228 in Figure 13B will increase compared to distance 228 in Figure 13A, and distance 229-S in Figure 13B will decrease relative to blade chord 186 compared to distance 229-S in Figure 13A. Conversely, if the angle of attack is maintained while moving deflector chord line away from the oncoming fluid flow 1, distance 228 in Figure 13A will decrease relative to blade chord 186 compared to distance 228 in Figure 13B.

[0342] While positioning the deflector forward of the rotor plane relative to the oncoming flow 1 (deflector 200) or aft of the rotor plane relative to the oncoming flow 1 (deflector 200-S) will result in improved performance (e.g., increased overall torque) of the blade-deflector assembly compared to a blade without a deflector, flow analysis indicates that positioning the deflector forward of the rotor plane relative to the oncoming flow 1 (deflector 200) results in further improved performance compared to positioning the deflector aft of the rotor plane relative to the oncoming flow 1 (deflector 200-S). Flow simulation studies indicate that when the deflector 200 is positioned closer to the oncoming flow 1 than the blade 111, continuing to advance the deflector chord line 258 toward the fluid flow 1 increases the overall torque, provided the optimization parameters remain constant or reasonably constant. 8.2 Vertical Oblique - Figure 13C

[0343] 13C, the deflector leading edge 208 may be aft of, flush with, or ahead of the blade trailing edge 174, or may be biased toward or away from the oncoming flow 1 (see FIG. 13A). The deflector leading edge 208 may be skewed relative to the blade trailing edge 174 such that the distance between the blade trailing edge 174 and the deflector leading edge 208 is not uniform along the deflector span 223 (see FIG. 9A). A deflector 200 is skewed when the chordwise spacing 229-A between the deflector leading edge 208 and the blade trailing edge 174 at the deflector tip end 218 is different from the chordwise spacing 229-E between the deflector leading edge 208 and the blade trailing edge 174 at the deflector hub end 214.

[0344] The chordwise spacing between the deflector leading edge 208 and the blade trailing edge 174 may be expressed as (i) a positive value when the deflector leading edge 208 is aft of the blade trailing edge 174 (i.e., the deflector leading edge 208 trails the blade trailing edge 174 relative to the direction of travel of the deflector / blade assembly), and (ii) a negative value when the deflector leading edge 208 is forward of the blade trailing edge 174 (i.e., the deflector leading edge 208 leads the blade trailing edge 174 relative to the direction of travel of the deflector / blade assembly), with a distance of zero being equivalent to no chordwise spacing between the deflector leading edge 208 and the blade trailing edge 174 (i.e., the deflector leading edge 208 neither leads nor trails the blade trailing edge 174 relative to the direction of travel of the deflector / blade assembly). It should be noted that neither the deflector leading edge 208 nor the blade trailing edge 174 are necessarily straight, however, in one embodiment, the shape of the deflector leading edge 208 conforms to any curvature or non-straight portion of the blade trailing edge.

[0345] Depending on where the deflector 200 is positioned relative to the blade 111, the vertical skew may increase or decrease the overall torque as desired, for example, to adjust the output performance of the wind turbine, per the designer's choice. 8.3 Horizontal Oblique - Figure 13D

[0346] 13D , the position of the leading edge 208 of the deflector 200 relative to the trailing edge 174 of the blade 111 may be (i) closer to the oncoming fluid flow 1 than the blade 111, as shown, represented as a positive distance (horizontal separation), or (ii) farther from the oncoming fluid flow 1 than the blade 111, represented as a negative distance (horizontal separation). A distance of zero between the leading edge 208 of the deflector 200 and the blade trailing edge 174 means that there is no horizontal separation between the deflector leading edge 208 and the blade trailing edge 174.

[0347] The horizontal distance 228-A between the deflector leading edge 208 and the blade trailing edge 174 at the deflector tip end 218 may be greater than, equal to, or less than the horizontal distance 228-B between the deflector leading edge 208 and the blade trailing edge 174 at the deflector hub end 214. Flow simulations indicate that a larger horizontal distance 228-A at the deflector tip end 218 relative to the horizontal distance 228-B at the deflector hub end 214 increases overall torque. Flow analysis indicates this is due to a much larger volume of fluid flowing between the deflector leading edge 208 and the blade trailing edge 174 (collectively, "edges") near their respective tip ends 151 and 218, as a result of their respective circumferential velocities, compared to a much smaller volume of fluid flowing between the edges near the deflector hub end 214.

[0348] The flow simulations also show that moving the deflector 200 closer to the oncoming fluid flow 1 than shown in Section 7 increases the overall torque. When the deflector 200 is located on the pressure side of the blade 111, the farther it is advanced outward from its position behind the blade 111 toward the oncoming fluid flow 1, the greater the volume of the fluid flow 1 that is available to increase the performance of the blade 111.

[0349] When deflector 200 is located on the pressure side 178 of blade 111, it creates a phenomenon similar to changing the environment in which blade 111 operates at higher fluid flow 1 velocities, e.g., wind speeds. This phenomenon increases as deflector 200 is moved closer to the oncoming fluid flow 1 as described above due to the increased fluid flow rate benefiting blade 111. 8.4 - Suction side deflector position - Figure 13E

[0350] 13E, flow simulations indicate that an overall torque improvement can be obtained when the deflector 200-S is located on the suction side 182 of the blade 111, with fewer concave surfaces 230-S and convex surfaces 238-S than when the deflector 200 is positioned on the pressure side 178 of the blade 111. This is because the deflector 200, when configured on the suction side 182 of the blade 111 as shown, and when used in conjunction with a deflector 200 located on the pressure side of the blade 111 (configuration not shown), acts more like a flow straightener than a deflector, thus reducing turbulence and suction near the suction surface 182 following the edge beneficial area 16 (see FIG. 2G). 9. Alternative Embodiments

[0351] The alternative embodiments described herein may be used in combination with any (i) fluid type, i.e., air and water, and (ii) any deflector / blade assembly or alternative embodiment thereof, i.e., deflector with curved tip (see Section 9.3) and fluid wall (see Section 9.5), regardless of any drawings or text describing such alternative embodiments. 9.1 Partial span deflector - Figure 14A - Figure 14E

[0352] The partial span deflector 200-A may embody all of the features and attributes of the deflector 200, including, but not limited to, the connector tube 270 and leading and trailing edge features as described in Section 6 and shown in Figures 9K, 9L, 9M, and 9N.

[0353] Partial span deflector 200-A may be retrofitted anywhere along the span of an existing turbine blade at the designer's option to increase turbine performance, for example, if the turbine is performing below its rated capacity. Flow simulations and physical testing indicate that partial span deflectors increase the overall torque per square area of ​​the pressure and suction surfaces of deflector 200-A similar to, but less than, deflector 200 extending substantially the full span of the blade. Flow simulations also indicate that partial span deflectors with longer spans produce greater overall torque per square area than partial span deflectors with shorter spans. Thus, flow simulations suggest that a longer deflector with twice the area of ​​a shorter deflector would more than double the overall torque compared to the shorter deflector.

[0354] Referring now to FIG. 14A, a partial span deflector 200-A is configured on the pressure side 178 of the blade 111 at approximately the midpoint between the blade tip 151 and the root end 158.

[0355] 14B, with still reference to FIG. 14A, partial span deflector 200-A is fixedly coupled to blade 111 via connector assembly 261-A, which includes fixedly coupled outer blade end flange 272-A. Connector assembly 261-A embodies the same aerodynamic characteristics as connector assembly 261 as described in Section 6 and shown in FIGS. 9K, 9L, 9M, 9N, including, but not limited to, that it (i) embodies two sets of leading and trailing edges, one set of leading and trailing edges being affected by and minimizing drag related to the oncoming fluid flow as described above, and a second set of leading and trailing edges being affected by and minimizing drag related to the fluid flow (apparent velocity), and (ii) has an elliptical and / or oval profile oriented to align with the rotational flow.

[0356] 14C and 14D, in one embodiment, connector assembly 261-A comprises a tube 270-A with a fixedly connected deflector end flange 271-A and a fixedly connected blade end (pressure side) flange 272-A, and one or more studs 291-A, 291-B, 291-C, and 291-D (collectively, "flange studs") protruding from and fixedly connected to blade end flange 272-A.

[0357] Still referring to FIG. 14C, and now referring to FIG. 14D, connector 261-A includes suction side flange 293-A and tubes 292-A, 292-B, 292-C, and 292-D (collectively, "flange tubes") that protrude from and are fixedly connected to suction side flange 293-A. Flange studs 291-A, 291-B, 291-C, 291-D (i) penetrate pressure surface 178 of blade 111, (ii) pass through flange pipes 292-A, 292-B, 292-C, 292-D (which penetrate suction surface 182 of blade 111) and suction side flange 293-A, and (iii) are secured using fasteners 295 (e.g., nuts on the threaded ends of flange studs 291-A, 291-B, 291-C, 291-D protruding from suction side flange 293-A) or other suitable means for securing the ends of flange studs 291-A, 291-B, 291-C, 291-D to suction side flange 293-A, such as welding or the like.

[0358] 14E, still referring to Figures 14C and 14D, the geometry (contour) of pressure side blade end flange 272-A and suction side flange 293-A matches the respective blade pressure surface 178 and suction surface 182 (see Figure 2B) with which they mate. Each flange stud length and corresponding flange pipe length may vary, i.e., the flanges may be tapered and / or twisted, to accommodate variations in the spacing between the blade pressure and suction surfaces that mate with flanges 272-A and 293-A, respectively.

[0359] The lengths of flange tubes 292-A, 292-B, 292-C, 292-D may be sized small compared to the spacing between blade pressure surface 178 and suction surface 182 (see FIG. 2C ) to achieve a compression fit between flanges 272-A and 293-A and blade 111 while preventing fastener 295 from compressing blade 111 beyond the designer's preference.

[0360] Additionally, the mechanical attachment of pressure side blade end flange 272-A and suction side flange 293-A may be chemically bonded or otherwise adhered to the exterior of blade 111, and the mechanical attachment of the flange tubes may be chemically bonded or otherwise adhered to the internal structure of blade 111 through which flange tubes 292-A, 292-B, 292-C, 292-D pass.

[0361] The connector assembly 261-A matches the twist of the deflector / blade assembly and the concave and convex surfaces of the deflector 200-A, and therefore the twist and / or length or angle of the connector assembly 261-A may vary over the deflector span 223 (see FIG. 9A).

[0362] Connector tube 270-A may embody all of the benefits and features of the leading and trailing edges of connector tube 270 as described in Section 6, including, but not limited to, two sets of leading and trailing edges. One set of leading and trailing edges acts against the oncoming wind flow when the blade / deflector assembly is stationary, and the other set of leading and trailing edges acts against the rotational flow while the blade / deflector assembly is rotating. 9.2 Deflectors of non-uniform thickness - Figure 15

[0363] 15 and 15 DETAILS A-C, an embodiment of deflector 200-B includes a pressure surface 204-B that may be essentially a mirror image of pressure surface 204 of deflector 200 of similar overall shape, size, and geometry (see FIG. 9A), but deflector 200-B is not of uniform thickness. Deflector 200-B differs from deflector 200 in that it has a more conventional airfoil shape than deflector 200 does, such that deflector 200-B is thicker between pressure surface 204-B and suction surface 206-B near leading edge 208-B and thinner between pressure surface 204-B and suction surface 206-B near trailing edge 212-B ("suction-side airfoils"). Deflector 200-B has a vane-shaped profile that generates a pressure differential on upstream (pressure) surface 204-B and downstream (suction) surface 206-B due to the relative fluid flow across the upstream and downstream surfaces. Pressure surface 204-B of deflector 200-B may have concave and / or convex surfaces 230 and / or 238, respectively, that are similar to or essentially identical to concave and / or convex surfaces 230 and / or 238 on pressure surface 204 of uniform thickness deflector 200 (see FIG. 9A).

[0364] The non-uniform thickness on the suction side may be used to increase the overall torque by generating differential upstream / downstream pressure (lift) depending on (i) the relative horizontal and vertical position of the deflector 200-B with respect to the blade 111 to which the deflector 200-B is fixedly or operably (adjustably) coupled, (ii) the shape and size, (iii) the angle of attack of the deflector 200-B, and (iv) the depth of the convex and concave surfaces (see Sections 3, 5 and 8.1).

[0365] The thickness between the pressure surface 204-B and the suction surface 206-B of the deflector 200-B may vary from the tip end 218-B of the deflector 200-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.

[0366] Deflector 200-B may be used in place of deflector 200 on the pressure side 178 or suction side 182 (see Figures 2A and 2B, respectively) of blade 111; however, due to the thickened profile of deflector 200-B, its suction side 206-B has different flow characteristics than deflector 200.

[0367] Deflector 200-B may have an internal structure similar to blade 111 (see Section 1 and FIG. 2C). 9.3 Curved Tip - Figure 16A

[0368] 16A and 16B, an embodiment of a deflector 200-C includes a curved section 219 along a portion of the trailing edge 212 that increases overall torque by reducing drag on the deflector 200-C. The terminal trailing edge angle at the tip 218 of the trapezoidal shaped deflector (see FIG. 9A) generates a negative torque. By eliminating this angle in the area of ​​the deflector tip 218, this negative torque can be reduced, resulting in a net increase in overall torque despite the reduced area of ​​the deflector. The angle is eliminated, or at least reduced in size, by deviating the shape of the trailing edge 212 so that the deflector chord is shorter at the deflector tip end 218 than it would be if the trailing edge shape was not deviated. For example, the trailing edge angle can be eliminated by providing a curved trailing edge section 219 that begins at or near the deflector leading edge 208 at the deflector tip end 218 and ends at a point 220 that can be located up to one-third of the distance between the deflector tip end 218 and the hub end 214.

[0369] The curved section 219 may be optimized to increase overall torque by changing the curvature and length of the curved section 219. Additionally, rather than a curved trailing edge section 219, a straight trailing edge section can be provided that begins at or near the deflector leading edge 208 at the deflector tip end 218 and ends at point 220. 9.4 Arced Tip - Figure 17A

[0370] 17A, an embodiment of deflector 200-D includes an arcuate tip section 231-D, which increases overall torque. The arcuate tip section 231-D is provided by deviating the shape of the trailing edge 212-D so that the deflector chord is longer at the deflector tip end 218-D than it would be if the trailing edge shape were not deviated. In this section, to facilitate readability and understanding, deflector 200-D is superimposed over an identically sized deflector 200, except for arcuate tip section 231-D, to show the un-deviant trailing edge 212 in dashed lines. As a result, in this section, any part number not followed by a hyphen and a letter refers to deflector 200 for comparison purposes. Additionally, for illustrative purposes, the end view and cross-sectional detail views (FIGS. 17B and 17C, respectively) have broad crosshatching to depict extended arcuate area 231-D and narrow crosshatching to depict portions of deflector 200 that are included to aid in understanding the extended arcuate tip area. The change in crosshatch direction does not have any significance with respect to the construction of deflector 200-D, as deflector 200-D may comprise a single, unitary structure, and is not necessarily intended to indicate that deflector 200-D is formed from multiple components and / or different materials in the area of ​​section 231-D.

[0371] Arcuate section 231-D extends from trailing edge 212 of deflector 200 (see also FIG. 9A ) and has an arcuate (or curved) trailing edge 212-D that defines a chord that gradually increases between leading edge 208 and arcuate trailing edge 212-D from intersection 234-D to tip end 218-D. Arcuate tip section 231-D includes a chord extension 232-D from trailing edge 212 to the extended tip trailing edge 212-D, and a length 233-D that extends from deflector tip end 218-D to intersection 234-D where arcuate section trailing edge 212-D intersects with trailing edge 212. Intersection 234-D may be located at any point along the span of deflector 200-D up to hub end 214-D.

[0372] Still referring to FIG. 17A, and now referring to FIG. 17B, arcuate tip section 231-D includes a convex surface 235-D on pressure side 204-D that extends between trailing edge 212-D and the extension of trailing edge 212-D to 212-D (see dashed line in FIG. 17A).

[0373] 17C, still referring to Figures 17B and 17A, beginning at deflector tip end 218-D, arcuate tip section 231-D essentially fills a space, depicted by broad crosshatching, bounded by an extension of trailing edge 212 (dashed line in Figure 17A), a portion of suction surface 206 proximate the extension of trailing edge 212, arcuate tip suction surface 206-D, arcuate tip pressure surface 204-D, and arcuate section trailing edge 212-D. The filled space can vary in width and curvature across the span of arcuate section 231-D, and therefore chord can correspondingly vary. Arcuate tip section 231-D is depicted as an extension of superimposed deflector 200, shown in narrow crosshatching.

[0374] In the embodiment shown, the cross-sectional area of ​​the arcuate tip section 231-D (thickness between the pressure surface 204-D and the suction surface 206-D) decreases from the deflector tip end 218-D to the intersection 234-D, following the deflector twist between the tip end 218-D and the hub end 214-D.

[0375] The curvature, length, and cross-sectional area of ​​curved section 231-D may be varied according to the designer's choice to increase the overall torque. 9.5 Fluid Walls - Figures 18A-18B

[0376] 18A and 18B, an embodiment of deflector 200-E includes one or more walls 600 projecting from one or both surfaces of deflector 200-E (shown projecting from pressure surface 204 in FIGS. 18A and 18B). Each wall 600 may extend from leading edge 208 to trailing edge 212, or any portion thereof, and may follow a distinct rotational path 275 about rotor axis of rotation 123 (see FIG. 1A), or may be linear or curved along an arc other than rotational path 275. Deflector 200-E may further include a transverse wall 620 extending from one or more walls 600 along or near trailing edge 212. Wall 600 and cross wall 620 are fixedly coupled to deflector 200-E and extend toward the oncoming fluid flow from pressure surface 204 or toward the downwind flow from suction surface 206 (see details A, B, and C in FIG. 9A showing suction surface 206). Walls 600, 620 may be perpendicular to pressure surface 204 and / or suction surface 206, or may be otherwise oriented.

[0377] The wall 600 reduces overflow of fluid moving from the deflector tip end 218 towards the hub end 214, moving the center of gravity (center of pressure) towards the tip end 218 of the blade 111, thereby increasing the overall torque.

[0378] Wall 600 may have a uniform or non-uniform height from the beginning of the wall to the 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, the "edges of wall 600"). The edges of wall 600 may be straight, tapered, beveled, or curved to reduce drag or otherwise improve performance characteristics, including, but not limited to, increasing overall torque.

[0379] The cross wall 620 reduces fluid overflow along the trailing edge 212, thereby increasing the overall torque. The height of the cross wall 620 may be the same as or different from the height of the wall 600. Although the configuration of the cross wall 620 may contribute to the drag of the rotating blade / deflector assembly, flow simulation results indicate that the performance improvement from the cross wall 620 outweighs the drag it induces.

[0380] The edges of the transverse wall 620 may be straight, tapered, beveled, or curved to reduce drag or otherwise improve performance characteristics.

[0381] Two or more walls 600 of various lengths and heights may be configured on the pressure side 204 of the deflector 200-E anywhere along the deflector span 223 (see FIG. 9A).

[0382] One or more transverse walls 620 of various lengths and heights may be configured along the deflector span 223 (see FIG. 9A) near the trailing edge 212. 9.6 Multi-section deflector and connector assembly - Figures 19A and 19B

[0383] The deflector and / or connector assembly may be provided in a multi-section arrangement. The multi-section deflector 201 (see FIG. 19A) and multi-section connector 261-B (see FIG. 19B) allow for a combination that (i) allows for the entire deflector to be deployed or replaced by simply removing pins or other similar fasteners from the multi-section connector 261-B, as described further below, (ii) in contrast to monolithic deflectors, the multi-section deflector 201 (see FIG. 19A) is deployed in sections, thus reducing the time, expense, and difficulty of transporting blade / deflector assemblies, and (iii) allows for simple replacement of a damaged deflector section, e.g., section 201-B (see FIG. 19A), when repair of a portion of the deflector and / or connector assembly is required. This feature is particularly beneficial because it allows connectors for deflectors designed to affect all or a large portion of the airfoil section 164 of the blade 111 (see FIG. 2A) to be fixedly coupled to internal structures within the blade during their manufacture. As a result, without this feature, repairing a damaged deflector would be more complicated and expensive. It is important to note that the illustration in FIG. 19A is of the suction side. As a result, the cut-away cross-section appears inverted.

[0384] As shown in Figure 19A, multi-section deflector 201 includes a plurality of adjacent sections 201-A through 201-E. In the illustrated embodiment, each section 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 a requirement. The geometry of a particular multi-section deflector 201, when assembled, may be substantially identical in all respects to the geometry of a single-piece deflector 200 of identical design (e.g., as shown in Figure 9A).

[0385] Adjacent sections of multi-section deflector 201, for example, sections 201-A and 201-B, sections 201-B and 201-C, sections 201-C and 201-D, and sections 201-D and 201-E, may be connected to each other by connectors that include interconnected parallel top and bottom plates between which abutting ends of adjacent sections are sandwiched and held together. For example, as shown in detail B of FIG. 19A , the connector for connecting sections 201-B and 201-C includes top plate 202-C and bottom plate 202-D, with the ends of sections 201-B and 201-C abutting each other and sandwiched between bottom plate 202-D and top plate 202-C. Relief is preferably provided on the top and bottom surfaces of the abutting ends of adjacent sections so that the bottom and top plates are substantially flush with the pressure surface 204 and suction surface 206 of the deflector 201.

[0386] 19A shows bottom plate 202-B of the connector connecting adjacent sections 201-A and 201-B, bottom plate 202-D of the connector connecting adjacent sections 201-B and 201-C, bottom plate 202-F of the connector connecting adjacent sections 201-C and 201-D, and bottom plate 202-H of the connector connecting adjacent sections 201-D and 201-E. As shown in Detail A of FIGS. 19A and 19A , the connectors may be oriented at an angle relative to a line extending between the leading and trailing edges of deflector 201-E (e.g., the chord line). Benefits of angled connections include making the section joints (i) self-aligning with the positive stops, thus allowing for faster and more precise placement and assembly compared to non-angled joints, and (ii) stronger due to the increased surface area provided by the increased length of each joint.

[0387] 19A and Detail A of FIG. 19A, a plurality of fasteners connect the top and bottom plates, thereby holding together adjacent sections sandwiched between the plates. For example, as shown in Detail B of FIG. 19A, mechanical fasteners 202-P (e.g., screws, bolts, rivets, or the like) connect top plate 202-C to bottom plate 202-D. One set of fasteners 202-P connecting top plate 202-C to bottom plate 202-D extends through the end of section 201-B, and another set of fasteners 202-P connecting top plate 202-C to bottom plate 202-D extends through the end of section 201-C. Adhesive may be used to secure the top plate 202-C and bottom plate 202-D to adjacent deflector sections (with or without fasteners 202-P), but the use of adhesive may mean that the top plate 202-C and bottom plate 202-D cannot be removed from the deflector to replace a damaged deflector section (as described above) simply by removing the fasteners 202-P. 9.6.1 Multipart Connectors

[0388] 19B, with still reference to FIG. 19A, in some embodiments, the connector tubes of connector assembly 261 may be separable into two or more parts. For example, as shown in FIG. 19B, multi-part connector assembly 261-B may include a first (or upper) tube section 270-A and a second (or lower) tube section 270-B connectable to first tube section 270-A. In one example, as shown in Details A and B of FIG. 19B, first and second tube sections 270-A, 270-B may be connected by a joint including a tongue 270-C received within a mating groove 270-D. Tongue 270-C is retained in groove 270-D by retainer pin 270-G, which extends through hole 270-F formed in the end of lower section 270-B on the opposite side from groove 270-D and is aligned with hole 270-E formed in tongue 270-C. In the illustrated embodiment, tongue 270-C is formed on first tube section 270-A and groove 270-D is formed on second tube section 270-B, although the components may be reversed, with tongue 270-C formed on second tube section 270-B and groove 270-D formed on first tube section 270-A.

[0389] The multi-section deflector can be delivered to the installation site in an unassembled state, and the sections 201-A through 201-E can be attached to one another by placing adjacent sections with their ends abutting one another and with the top and bottom plates 202-C, 202-D of the associated connector assemblies located above and below the abutting ends. Holes aligned with fastener holes formed in the top and bottom plates 202-C, 202-D may be pre-formed in the abutting deflector sections or formed (e.g., drilled) on-site, and fasteners 202-P inserted through the aligned holes. A 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 blade to which the deflector 201 is to be attached. The first section 270-A is connected to the second section by, for example, the tongue 270-C, groove 270-D, and retainer pin 270-D described above.

[0390] To replace one or more sections of multi-section deflector 201, connector assembly fasteners 202-P holding the section to be replaced are removed, and when any section to be replaced is connected to connector assembly 261-B, retainer pins 270-G are removed, allowing upper section 270-A to be separated from lower section 270-B. The replacement section is then placed in place, with its ends positioned between top plate 202-C and bottom plate 202-D of the connector assembly and abutting the ends of the adjacent deflector section, and tongues 270-C seated in grooves 270-D. Fasteners 202-P are installed through the ends of the replacement section into top plate 202-C and bottom plate 202-D, and retainer pins 270-G are inserted into aligned holes 270-F and 270-E in tube sections 270-A and 270-B. A retainer 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, other methods may be used by those skilled in the art, including clevis pins, detent clevis pins, safety pins, nuts, and bolts. 9.7 Variable Angle Connector Assembly - Figures 20A-20I

[0391] 20A, one deflector embodiment includes a powered variable angle connector assembly (VAC assembly) capable of changing the deflector angle of attack. This embodiment can (i) control and / or improve deflector / blade assembly performance over the range of fluid velocities in which the assembly is operating, (ii) cause blades benefiting from the deflector to begin rotating and convert kinetic energy faster than they would otherwise, as flow simulations and physical testing indicate, and (iii) act as a braking device.

[0392] Still referring to FIG. 20A, in one embodiment, VAC assembly 261-E, visible on suction side 206 of deflector 200 and suction side 182 of blade 111, is fixedly coupled within blade 111 and fixedly coupled to deflector 200. Connector assembly 261-E conforms to the twist of the deflector / blade assembly and the concave and convex surfaces of deflector 200, and thus the twist and / or length or angle of connector assembly 261-E may vary across deflector span 223 (see FIG. 9A).

[0393] VAC assembly 261-E connects deflector 200 to blade 111 and is configured to enable and provide motorized adjustment of the deflector angle of attack, as will be described. Such motorized adjustment may be automated and computer controlled.

[0394] As explained in Section 8.1, changing the angle of attack of the deflector 200 is one variable that affects the effect of the deflector on the blades 111 and, therefore, the overall performance of the deflector / blade assembly and rotor. 9.7.1 Optimization Position - Figure 20B

[0395] 20B, still referring to FIG. 20A, the deflector chord line 258 is depicted at five positions relative to the rotor rotation plane 104, represented as 10° angular ranges 263-A, 263-B, 263-C, and 263-D. To improve the clarity of the illustration in FIG. 20B, the profile of the deflector 200 is not shown. The deflector trailing edge would be located in the area 212-T, located near the upper portion of FIG. 20B, and the deflector leading edge would be located in the area 208-L, located near the lower portion of FIG. 20B. In this embodiment, the deflector 200 articulates about point 262 (see also FIG. 20C) and has performance characteristics associated with the deflector angle of attack (“AoA”) and position as follows: [Table 7]

[0396] 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 throughout the speed range. For example, physical testing has shown that at wind speeds insufficient to begin rotating a blade without a deflector, a blade benefiting from a deflector begins to rotate sooner at the same wind speed, e.g., less than 1.12 m / s compared to about 2.25 m / s for a blade without the benefit of a deflector, and outperforms the blade without the benefit of a deflector throughout the speed range. However, if the deflector angle of attack is moved to position 265 under conditions where the speed of the oncoming fluid flow 1 was 0.0 to 0.9 m / s, the rotor would begin to rotate at 0.67 m / s, and as the speed of the oncoming fluid flow 1 increases, by adjusting the deflector angle of attack from position 265 to position 266, additional overall torque would be obtained due to the deflector 200 having an optimal angle of attack throughout the entire speed range of the blade 111. 9.7.2 Detailed Operational Overview - Figures 20C and 20D

[0397] 20C and 20D, with still reference to FIG. 20B, cutaway cross sections reveal the motor drive components and deflector-VAC connector connection. FIG. 20C shows the deflector in a fully extended position 264 (representing one end of the deflector angle of attack range), and FIG. 20D shows the deflector in a fully retracted position 267 (representing the opposite end of the deflector angle of attack range). Note that the term “fully extended” refers to the position of the deflector relative to the plane of rotation 104 (see FIG. 20B). Consequently, in the embodiment shown, when the deflector 200 is in its fully extended position, the flexible shaft assembly 550 is in its fully retracted position, and similarly, when the deflector 200 is in its fully retracted position, the flexible shaft assembly 550 is in its fully extended position.

[0398] Connector assembly 261-E includes a pivoting spar 270-H having a flange 272-H at one end that is connected (e.g., by a mechanical fastener or the like) to a U-shaped web 116 in blade 111. Pivoting spar 270-H protrudes through an opening in blade 111 at or near trailing edge 174 of the blade and extends to a location spaced aft of blade trailing edge 174. Deflector end flange 271-H is attached to deflector 200 and includes a pivoting connection 262 where an end of spar 270-H is pivotally connected to flange 271-H. Details of this connection are described in Section 9.7.4.

[0399] In the illustrated embodiment, spar 270-H is connected to flange 271-H (and thus to deflector 200) closer to deflector trailing edge 212 than to deflector leading edge 208. Flexible shaft assembly 550 is connected to flange 271-H closer to deflector leading edge 208 than to deflector trailing edge 212 and is configured to pivot deflector 200 about the end of pivoting spar 270-H at pivot connection 262, thereby selectively altering the angle of attack of deflector 200.

[0400] In the illustrated embodiment, motor 650 rotates shaft 652, which drives right-angle drive 655, which rotates drive screw 656, thereby causing corresponding axial movement of collar 670 along the length of drive screw 656, which causes corresponding axial movement of male guide tube 680 (see also Section 9.7.6), which extends and retracts flexible shaft assembly 550 and alters the angle of attack of deflector 200. In this embodiment, motor 650 is located proximate the hub end of blade 111; however, motor 650 may alternatively be located anywhere along blade span 154 (see FIG. 2A) or within hub 121 (see FIG. 1A).

[0401] The 40° range of motion of the VAC connector (see FIG. 20B) may be extended in a number of ways, including (i) moving pivot point 262 closer to pivot point 563, or (ii) lengthening screw 656 and positioning motor 650, shaft 652, right-angle drive 655, shaft 660, and the remainder of the associated shafts and right-angle drives (see FIG. 20E) below support 119 to increase the curvature of spar 270-H and therefore increase the travel distance between trailing edge 208 and pivoting spar 270-H, or (iii) swapping the locations of pivot points 262 and 563, or (iv) any combination of methods (i)-(iii).

[0402] Flexible shaft assembly 550 includes a flexible shaft 566 that is pivotally connected at one end to flange 271-H and anchored at an opposite end within blade 111. Flexible shaft 566 extends through a flexible shaft guide tube 565, which in the illustrated embodiment is part of pivot spar 270-H. The end of flexible shaft 566 that is anchored within blade 111 is coupled to a drive screw assembly 665 (see FIG. 20H ) that is configured to provide powered (e.g., motor-driven) axial movement of flexible shaft 566 to vary the amount that flexible shaft 566 extends from blade 111 and thus pivot deflector 200 to which flexible shaft 566 is attached about pivot connection 262 to alter the angle of attack of deflector 200, as will be described. 9.7.3 Major Drivetrain Components - Figure 20E

[0403] Still referring to FIG. 20C, and now referring to FIG. 20E, if the deflector / blade assembly includes multiple VAC connector assemblies 261-E, the right-angle drive 655 may also rotate a shaft 660, which is connected to the subsequent right-angle drive for the adjacent VAC connector assemblies 261-E, so that a single motor 650 can actuate all of the VAC connector assemblies 261-E simultaneously.

[0404] The illustrated right-angle drive and associated drive shaft configuration may be repeated along the length of deflector span 223 (see FIG. 9A), subsequently driving each subsequent VAC connector assembly 261-E. In this embodiment, motor 650 drives shaft 652, which drives right-angle drive 655, screw 656, and shaft 652-A, which drives right-angle drive 655-A, screw 656-A, and shaft 652-B, which drives right-angle drive 655-B, screw 656-B, and shaft 652-C, which drives right-angle drive 655-C, screw 656-C, and shaft 652-D, which drives right-angle drive 655-D and screw 656-D.

[0405] Other embodiments of the VAC connector may include one or more motors (not shown) similar to motor 650 located anywhere along blade span 154 (FIG. 2A), for example, near the middle of blade span 154 or within hub 121 (see FIG. 1A). Similarly, a computer controlling motor 650 may be located anywhere within turbine 100 (see FIG. 1A). 9.7.4 VAC Pivot Details - Figure 20F

[0406] 20F, pivoting spar 270-H pivots at pivot point 262 about pivot axis 262-A. In one embodiment, pivot point 262 (see FIGS. 20C and 20D), which is collinear with pivot axis 262-A, may include spaced spar brackets 501 protruding from flange 271-H. Bushings 504 are press-fit into holes 503 formed in the ends of spar 270-H, the ends of spar 270-H are received between spar brackets 501, and bushings 504 and holes 503 are aligned with holes 502 formed in spar brackets 501. A bushing 505 (which may be a self-lubricating bushing) is inserted into one end of bushing 504 through one hole 502, and a top hat bushing 506 is inserted into the opposite end of bushing 504 through the opposite hole 502, preferably contacting bushing 505 within bushing 504. A bolt 507 is inserted through hole 502 and bushings 506 and 505 and is secured at the end by a nut 508. A bolt and nut is one method of attachment that may be used at pivot points 262 and 563 (see FIGS. 20C and 20D). However, other methods, including clevis pins, detent clevis pins, and safety pins, may be used by one skilled in the art. 9.7.5 Flexible Shaft Pivot Points and Shaft Details - Figures 20F-20G

[0407] 20G, with still reference to FIG. 20F, in one embodiment, flexible shaft 566 is pivotally attached to flange 271-H at pivot point 563 (see FIG. 20C) and pivots about pivot axis 563-A at a pivot connector that is spaced in the deflector chord direction toward deflector leading edge 208 from pivot connector 262 (see FIG. 20C), connecting spar 270-H to the deflector at pivot point 262 (see FIG. 20C). Pivot point 563 (see FIG. 20C) may comprise a spaced flexible shaft bracket 561 that protrudes from flange 271-H. A bushing 570 is press-fit into a hole 560-A formed through a connector cap 560 disposed on the end of flexible shaft 566, with connector 560 received between flexible shaft brackets 561, with bushing 570 and hole 560-A aligned with a hole 562 formed in flexible shaft bracket 561. A first bushing 572 (which may be a self-lubricating bushing) is inserted into one end of bushing 570 through one hole 562, and a second bushing 572-A is inserted into the opposite end of bushing 570 through the opposite hole 562, preferably contacting first bushing 572 within bushing 570. A bolt 575 is inserted through hole 562 and bushings 572 and 572-A and secured at the ends by a nut 578.

[0408] One or more seals or other means may be provided to prevent the penetration of moisture or debris along the flexible shaft 566 and into the flexible shaft guide tube 565. As shown in FIGS. 20F and 20G, an O-ring 542 may be provided that surrounds the flexible shaft 566 and is positioned within an O-ring seat 544. The O-ring 542 is one design for preventing fluid from entering the flexible shaft guide tube 565; however, multiple types and numbers of seals may be used by one skilled in the art for this purpose. 9.7.6 Guide Tube Assembly Details - Figure 20H-Figure 20I

[0409] 20H, the end of flexible shaft assembly 550 is mounted within blade 111 (see FIGS. 20C and 20D) for limited axial movement in guide tube assembly 690. Guide tube assembly 690, including guide tube housing 692, may be secured between webs 116 and 117 by bolt 287 extending through flange 271-H, web 116, through hole 688 formed in housing 692, web 117, and lower flange 281-A. Bolt 287 may be secured by a nut (not shown), or lower flange 281-A may be threaded.

[0410] Flexible shaft 566 is disposed within guide tube bore 685 (see FIG. 20I) in guide tube housing 692. A stop at 555 fixedly attached at the end of flexible shaft 566 has a diameter slightly smaller than the diameter of bore 685, but larger than the diameter of the bore formed in web 116 and flange 272-H (which diameter is slightly larger than the diameter of flexible shaft 566), to allow axial movement of stop 555 and flexible shaft 566 within bore 685. Stop 555 contacts web 116 and, in conjunction with stop 681, described below, prevents flexible shaft 566 from being withdrawn from guide tube housing 692.

[0411] A flexible shaft actuator is coupled to flexible shaft 566 and provides selective powered (e.g., motor-driven) axial movement of flexible shaft 566 within guide bore 685. In the illustrated embodiment, the flexible shaft actuator comprises a drive screw assembly 665. Drive screw assembly 665 comprises a male guide tube 680 that is disposed for axial movement within guide tube bore 685.

[0412] Drive assembly 665 further includes a drive screw 656 extending into an axial blind bore formed in male guide tube 680. A collar 670 with a ball screw bearing 671 is operably coupled to drive screw 656 such that rotation of drive screw 656 causes corresponding axial movement of collar 670 along the length of drive screw 656. Collar 670 may abut and be connected to stop 681 of male guide tube 680 such that axial movement of collar 670 along drive screw 656 causes corresponding axial movement of male guide tube 680. The end of male guide tube 680 opposite stop 681 may abut and be connected to stop 555 of flexible shaft 566 such that axial movement of male guide tube 680 causes corresponding axial movement of flexible shaft 566 within guide tube bore 685. When flexible shaft 566 is fully extended, stop 681 contacts flange 281-A, thus limiting its travel in conjunction with stop 555 as described above. Guide tube housing 692 may be split longitudinally and fastened together (not shown) to facilitate assembly of flexible shaft assembly 550 and drive screw assembly 665.

[0413] 20I, keys 682, 683, received in key slots 682-A, 683-A, respectively, prevent male guide tube 680 from rotating within guide tube bore 685. A stop 681 at the lower end of male guide tube 680 contacts the bottom of female guide tube 693, which is disposed within housing 692, to limit the travel of male guide tube 680 within bore 685 and, in turn, flexible shaft assembly 550 (see FIG. 20G). Male guide tube 680 and female guide tube 693 may be constructed from or consist of materials of the designer's choice, including low-friction, high-strength metals and plastics, for example, oil-impregnated sintered bronze and acetal homopolymers such as Delrin®. 10. Blades and Deflectors - Geometry as Simulated - Figures 21A-21D

[0414] Included in the following sections are CAD dimensional data for the deflector 111 and the position of the deflector 200 relative to the blade 111 when it is subjected to flow simulation as described in Section 7. 10.1 Deflector Dimensional Data - Figures 21A-21D

[0415] Referring now to FIG. 21A, a side profile schematic of an embodiment of deflector 200 is shown showing eleven reference points 900-910 along the chord beginning at point 900 at leading edge 208 to point 910 at trailing edge 212.

[0416] Still referring to FIG. 21A, and now referring to FIG. 21B, this table provides profile dimensional data for the deflector modeled for flow analysis in X and Y coordinates for profiles A, B, C, D, and E (leading edge 208 is the origin (0,0) of the coordinate system).

[0417] 21A and 21B, and now referring to FIG. 21C, a front view of deflector 200 shows the intersections from which the profile measurements in the table of FIG. 21B were made. Cross sections AA, BB, CC, DD, and EE in FIG. 21C correspond to columns A, B, C, D, and E, respectively, of the table of FIG. 21B.

[0418] FIG. 21D shows a table of offset dimensions in the Z (spanwise) direction from the blade tip (from profile A, which corresponds to cross section AA in FIG. 21C, to profiles B, C, D, and E, which correspond to cross sections BB, CC, DD, and EE in FIG. 21C, respectively).

[0419] 21A-21D, geometric dimensional data for deflector 200 may be obtained at reference points 900-910 in FIG. 21A on each of profiles AE, which correspond to cross sections AA, BB, CC, DD, and EE, respectively, in FIG. 21C. For example, from FIGS. 21B and 21D, reference point 901 on profile B has (X, Y, Z) coordinates (dimensional data) relative to leading edge 208 at the tip end of deflector 200 (i.e., profile A) of (0.142 m, 0.008 m, 9.113 m). 10.2 Deflector Position Relative to Blade - Figures 22A-22B

[0420] 22A, the blade 111 and deflector 200, for which dimensional data is obtained from Section 10.1, are positioned in planes X, Y, and Z with the origin at the center of the connecting structure (hub mounting flange) 157. The deflector 200 is constrained by angle A (the trailing edge of the deflector 200 at the tip end of the deflector), angle B (the trailing edge of the deflector 200 at the hub end of the deflector), and angle C (the leading edge of the deflector 200 at the hub end of the deflector), thus defining each corner in X, Y, and Z coordinates and therefore completely defining the deflector 200 in three-dimensional space necessary to obtain the dimensional data.

[0421] 22B provides the X, Y, and Z coordinates (dimension data) for corners A, B, and C relative to the coordinate system origin centered at hub flange 157. The X, Y, and Z coordinates (dimension data) for corner A are (0.66 m, 2.07 m, 44.32 m), for corner B are (-0.43 m, 5.18 m, 7.89 m), and for corner C are (-0.80 m, 2.69 m, 7.80 m).

[0422] With respect to the positioning profile A-E of the deflector 200 in three-dimensional space, the geometric path of the blade trailing edge 174 in three-dimensional space can be followed as a guide for the leading edge 208 of the deflector 200. Cross sections A-A, B-B, C-C, D-D, and E-E of FIG. 21C can be spaced along the three-dimensional geometric path at Z intervals defined in FIG. 21D. In addition, a profile twist of 1° occurs between profiles A and E, gradually moving away from the oncoming flow. For example, the twist is profile A=0.0°, B=0.25°, C=0.5°, D=0.75°, and E=1.0°.

[0423] The vertical and horizontal skew distances of the deflector 200 between the blade trailing edge 174 and the deflector leading edge 208 as described in Sections 8.2-8.3 and shown in Figures 13C and 13D are -0.043 m at 229-A, 0.151 m at 229-E, 0.562 m at 228-A, and 0.252 m at 228-B. (Combination of elements and components)

[0424] All possible combinations of the elements and components described herein and / or recited in the claims are contemplated and considered part of this disclosure. It should be understood that all combinations of the concepts and additional concepts discussed in more detail herein (provided that such concepts are not mutually inconsistent) are contemplated as being part of the inventive subject matter described herein. Illustrative Embodiments

[0425] 1. A fluid-flow turbine blade assembly comprising: a rotor blade having a root section at which the rotor blade is attached to a hub of a fluid-flow turbine; a working section, the working section having a leading edge and a trailing edge, the working section configured and oriented to form a pressure surface facing an oncoming fluid flow impinging on the rotor blade and a suction surface; and 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, the deflector having 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, the deflector having a substantially uniform thickness between the upstream and downstream surfaces, at least a portion of the upstream surface along at least a portion of the span of the deflector having a concave shape in the chordwise direction, the trailing edge of the deflector being mounted aft of the trailing edge of the working section relative to a direction of travel of the turbine blade assembly.

[0426] 2. A fluid flow turbine blade assembly as described in embodiment 1, wherein the working section of the blade is an airfoil section or a hydrofoil section.

[0427] 3. A 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 the chord direction.

[0428] 4. A fluid flow turbine blade assembly according to any one of embodiments 1-3, wherein the portion of the upstream surface having the concave shape extends to the trailing edge of the deflector.

[0429] 5. A fluid flow turbine blade assembly as described in embodiment 3, wherein the portion of the upstream surface having the convex shape extends to the leading edge of the deflector.

[0430] 6. A fluid flow turbine blade assembly as described in any one of embodiments 1-5, 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.

[0431] 7. A fluid flow turbine blade assembly as described in 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.

[0432] 8. A fluid flow turbine blade assembly as described in any one of embodiments 1-5, 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.

[0433] 9. A fluid flow turbine blade assembly as described in embodiment 8, 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.

[0434] 10. A fluid flow turbine blade assembly according to any one of embodiments 1-9, wherein the leading edge of the deflector is mounted aft of the trailing edge of the working section relative to the direction of travel of the turbine blade assembly.

[0435] 11. The fluid flow turbine blade assembly of any one of embodiments 1-10, further comprising a connector assembly connecting the deflector to the rotor blade.

[0436] 12. A fluid flow turbine blade assembly as described in embodiment 11, wherein the connector assembly comprises a tube, a deflector end flange fixedly coupled to one end of the tube and the deflector, and a blade end flange fixedly coupled to an opposite end of the tube and the rotor blade.

[0437] 13. A fluid flow turbine blade assembly as described in embodiment 12, wherein the turbine blade assembly is mounted to a hub of a rotor rotatable about the rotor axis of rotation, the turbine blade assembly being axially oriented relative to the rotor axis of rotation, at least a portion of an oncoming fluid flow being parallel to the rotor axis of rotation, a first cross section of the tube defining an aerodynamic shape that tapers toward a first leading edge of the first cross section and toward a first trailing edge of the first cross section, relative to the oncoming fluid flow, and a second cross section of the tube defining an aerodynamic shape that tapers toward a second leading edge of the second cross section and toward a second trailing edge of the second cross section, relative to the fluid flow resulting from rotation of the rotor.

[0438] 14. A fluid flow turbine blade assembly as described in embodiment 13, wherein the first cross section is symmetrical about a line that bisects the first cross section between the first leading edge and the first trailing edge, and the second cross section is symmetrical about a line that bisects the second cross section between the second leading edge and the second trailing edge.

[0439] 15. The fluid-flow turbine blade assembly of any one of embodiments 12-14, comprising two or more connector assemblies, each of the two or more connector assemblies being positioned at a different spanwise position along the turbine blade assembly, and the tubes of each connector assembly being shaped between opposing ends of the tubes 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.

[0440] 16. A fluid flow turbine blade assembly according to any one of embodiments 1-15, wherein the spacing between the deflector and the rotor blade is constant across the span of the deflector.

[0441] 17. A fluid flow turbine blade assembly according to any one of embodiments 1-15, wherein a spacing between the deflector and the rotor blade varies across at least a portion of the span of the deflector.

[0442] 18. A fluid flow turbine blade assembly according to any one of embodiments 1-17, wherein at least one of a radius of curvature and an arc length of the portion of the upstream surface having a concave shape varies along at least a portion of the span of the deflector.

[0443] 19. A fluid flow turbine blade assembly according to any one of embodiments 1-18, wherein at least a portion of the 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 an upstream surface of the deflector and a downstream surface of the deflector.

[0444] 20. The fluid flow turbine blade assembly of embodiment 19, wherein at least 25-90% of the 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.

[0445] 21. A fluid flow turbine blade assembly as described in embodiment 20, wherein at least 25-80% of the chord extending between the leading edge of the deflector and the trailing edge of the deflector is located outside the profile of the deflector defined between the upstream surface of the deflector and the downstream surface of the deflector at the tip end of the deflector, and at least 65-90% of the chord extending between the leading edge of the deflector and the trailing edge of the deflector is located outside the profile of the deflector defined between the upstream surface of the deflector and the downstream surface of the deflector at the hub end of the deflector.

[0446] 22. A fluid flow turbine blade assembly according to any one of embodiments 1-21, wherein the spanwise curvature of the leading edge of the deflector follows the spanwise curvature of the trailing edge of the blade.

[0447] 23. A fluid flow turbine blade assembly according to any one of embodiments 1-22, further comprising one or more walls protruding from at least one of the upstream surface and the downstream surface of the deflector, each wall extending at least partially from a leading edge of the deflector to a trailing edge of the deflector.

[0448] 24. A fluid flow turbine blade assembly as described in embodiment 23, further comprising a transverse wall extending from at least one of the one or more walls, the transverse wall extending along or near the trailing edge of the deflector.

[0449] 25. A fluid flow turbine blade assembly according to any one of embodiments 1-24, wherein the deflector comprises two or more sections, each section connected to an adjacent section by a connector comprising top and bottom plates overlapping abutting ends of the section and adjacent sections, and fasteners extending through the top and bottom plates and portions of the section and adjacent sections where the top and bottom plates overlap.

[0450] 26. The fluid flow turbine blade assembly of any one of embodiments 1-25, wherein the deflector has a cambered mean line, a center of curvature of a first portion of the cambered mean line being located on a downstream side of the deflector, and a center of curvature of a second portion of the cambered mean line being located on an upstream side of the deflector.

[0451] 27. A fluid flow turbine assembly according to any one of embodiments 1-26, 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.

[0452] 28. A fluid flow turbine assembly as described in embodiment 27, wherein at a hub end of the deflector, at least one of a leading edge of the deflector and a trailing edge of the deflector is less proximate to the oncoming flow than at least one of a leading edge of the blade and a trailing edge of the blade.

[0453] 29. A fluid flow turbine assembly as described in embodiment 28, wherein the distance that the deflector is closer to the oncoming flow than the blades increases continuously from the hub end of the deflector to the tip end of the deflector.

[0454] 30. The fluid flow turbine blade assembly of any one of embodiments 11-15, 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.

[0455] 31. A fluid flow turbine blade assembly as described in embodiment 11, wherein the connector assembly comprises a variable angle connector assembly connecting the deflector to the rotor blade such that an angle of attack of the deflector relative to the rotor rotation plane is variable, the variable angle connector assembly comprising: 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 a 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 to effect axial movement of the flexible shaft.

[0456] 32. A fluid flow turbine assembly according to embodiment 31, wherein the flexible shaft actuator comprises: a guide tube assembly, the guide tube assembly being disposed within the rotor blade, the guide tube assembly comprising a guide tube housing having a guide bore in which a first end of the flexible shaft is supported and a guide tube movable within the guide bore, the first end of the flexible shaft being coupled to an end of the guide tube; a drive screw, the drive screw extending into a bore 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 a length of the drive screw, the threaded collar coupled to the guide tube such that axial movement of the collar is transmitted to the guide tube, causing axial movement of the guide tube within the guide bore, which in turn causes corresponding axial movement of the flexible shaft; and a motor, the motor coupled to the drive screw to provide powered rotation of the drive screw.

[0457] 33. A fluid flow turbine assembly as described in 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 for rotating the drive screw and in a second direction for rotating the drive shaft to transmit the rotation to a flexible shaft actuator of an adjacent variable angle connector assembly.

[0458] 34. A fluid flow turbine blade assembly according to any one of embodiments 1-33, wherein the deflector extends spanwise along the entire span of the rotor blade, including the root section and the working section.

[0459] 35. A fluid flow turbine blade assembly as described in any one of embodiments 1-34, wherein at least a portion of the trailing edge of the deflector includes a curved section of decreasing chord length between the leading edge of the deflector and the trailing edge of the deflector, the curved section extending to a tip of the deflector.

[0460] 36. A fluid flow turbine blade assembly as described in any one of embodiments 1-34, wherein at least a portion of the trailing edge of the deflector includes an arcuate section of increasing chord length between the leading edge of the deflector and the trailing edge of the deflector, the arcuate section extending to a tip of the deflector.

[0461] 37 A fluid-flow turbine blade assembly, comprising: a rotor blade, the rotor blade comprising: a root section, where the rotor blade is mounted to a hub of a fluid-flow turbine; a working section, the working section having a leading edge and a trailing edge, the working section configured and oriented to form a pressure surface and a suction surface facing an oncoming fluid flow impinging on the rotor blade; and a deflector, the deflector coupled to the rotor blade and extending spanwise along at least a portion of the working section of the rotor blade, the deflector deflecting the leading edge, the trailing edge, and the oncoming fluid flow. a deflector having an upstream surface facing toward the oncoming fluid flow and a downstream surface facing away from the oncoming fluid flow, at least a portion of a chord extending between a leading edge of the deflector and a trailing edge of the deflector being positioned outside a profile of the deflector defined between the upstream surface of the deflector 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 having a concave shape in the chord direction, the trailing edge of the deflector being mounted aft of the trailing edge of the working section relative to a direction of travel of the turbine blade assembly.

[0462] 38. A fluid flow turbine blade assembly as described in embodiment 37, wherein the working section of the blade is an airfoil section or a hydrofoil section.

[0463] 39. A 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 chord direction.

[0464] 40. A fluid flow turbine blade assembly according to any one of embodiments 37-39, wherein the portion of the upstream surface having the concave shape extends to the trailing edge of the deflector.

[0465] 41. A fluid flow turbine blade assembly as described in embodiment 39, wherein the portion of the upstream surface having the convex shape extends to the leading edge of the deflector.

[0466] 42. A fluid flow turbine blade assembly according to any one of embodiments 37-41, wherein along at least a portion of the span of the deflector, a leading edge of the deflector is closer to the oncoming fluid flow than a trailing edge of the rotor blade.

[0467] 43. A fluid flow turbine blade assembly as described in 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.

[0468] 44. A fluid flow turbine blade assembly according to any one of embodiments 37-41, wherein along at least a portion of the span of the deflector, a leading edge of the deflector is farther from the oncoming fluid flow than a trailing edge of the rotor blade.

[0469] 45. A fluid flow turbine blade assembly as described in 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.

[0470] 46. ​​A fluid flow turbine blade assembly according to any one of embodiments 37-45, wherein the leading edge of the deflector is mounted aft of the trailing edge of the working section relative to the direction of travel of the turbine blade assembly.

[0471] 47. A fluid flow turbine blade assembly according to any one of embodiments 37-46, wherein at least 25-90% of the chord extending between the leading edge of the deflector and the trailing edge of the deflector is located outside of a profile of the deflector defined between the upstream surface of the deflector and the downstream surface of the deflector.

[0472] 48. A fluid flow turbine blade assembly as described in embodiment 20, wherein at least 25-80% of a chord extending between the leading edge of the deflector and the trailing edge of the deflector is located outside a profile of the deflector defined between the upstream surface of the deflector and the downstream surface of the deflector at a tip end of the deflector, and at least 65-90% of a chord extending between the leading edge of the deflector and the trailing edge of the deflector is located outside a profile of the deflector defined between the upstream surface of the deflector and the downstream surface of the deflector at a hub end of the deflector.

[0473] 49. A fluid flow turbine blade assembly according to any one of embodiments 37-48, wherein the spanwise curvature of the leading edge of the deflector follows the spanwise curvature of the trailing edge of the blade.

[0474] 50. A fluid flow turbine blade assembly according to any one of embodiments 37-49, further comprising one or more walls protruding from at least one of the upstream surface and the downstream surface of the deflector, each wall extending at least partially from a leading edge of the deflector to a trailing edge of the deflector.

[0475] 51. A fluid flow turbine blade assembly as described in embodiment 50, further comprising a transverse wall extending from at least one of the one or more walls, the transverse wall extending along or near the trailing edge of the deflector.

[0476] 52. A fluid flow turbine blade assembly according to any one of embodiments 37-51, wherein the deflector comprises two or more sections, each section connected to an adjacent section by a connector comprising a top plate and a bottom plate overlapping abutting ends of the section and adjacent section, and fasteners extending through the top plate and bottom plate and portions of the section and adjacent section where the top plate and bottom plate overlap.

[0477] 53. A fluid flow turbine blade assembly according to any one of embodiments 37-52, wherein the deflector has a cambered mean line, a center of curvature of a first portion of the cambered mean line being located on a downstream side of the deflector, and a center of curvature of a second portion of the cambered mean line being located on an upstream side of the deflector.

[0478] 54. A fluid flow turbine assembly as described in any one of embodiments 37-53, 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.

[0479] 55. A fluid flow turbine assembly as described in embodiment 54, wherein at a hub end of the deflector, at least one of a leading edge of the deflector and a trailing edge of the deflector is less proximate to the oncoming flow than at least one of a leading edge of the blade and a trailing edge of the blade.

[0480] 56. A fluid flow turbine assembly as described in embodiment 55, wherein the distance that the deflector is closer to the oncoming flow than the blades increases continuously from the hub end of the deflector to the tip end of the deflector.

[0481] 57. A fluid flow turbine blade assembly according to any one of embodiments 32-56, further comprising a connector assembly connecting the deflector to the rotor blade.

[0482] 58. A fluid flow turbine blade assembly as described in embodiment 57, wherein the connector assembly comprises a tube, a deflector end flange fixedly coupled to one end of the tube and the deflector, and a blade end flange fixedly coupled to an opposite end of the tube and the rotor blade.

[0483] 59. A fluid flow turbine blade assembly as described in embodiment 58, wherein the turbine blade assembly is mounted to a hub of a rotor rotatable about the rotor rotation axis, the turbine blade assembly being axially oriented relative to the rotor rotation axis, at least a portion of an oncoming fluid flow being parallel to the rotor rotation axis, a first cross section of the tube defining an aerodynamic shape that tapers toward a first leading edge of the first cross section and toward a first trailing edge of the first cross section, relative to the oncoming fluid flow, and a second cross section of the tube defining an aerodynamic shape that tapers toward a second leading edge of the second cross section and toward a second trailing edge of the second cross section, relative to the fluid flow resulting from rotation of the rotor.

[0484] 60. A fluid flow turbine blade assembly as described in embodiment 59, wherein the first cross section is symmetrical about a line that bisects the first cross section between the first leading edge and the first trailing edge, and the second cross section is symmetrical about a line that bisects the second cross section between the second leading edge and the second trailing edge.

[0485] 61. A fluid-flow turbine blade assembly according to any one of embodiments 58-60, comprising two or more connector assemblies, each of the two or more connector assemblies being positioned at a different spanwise position along the turbine blade assembly, and the tubes of each connector assembly being shaped between opposing ends of the tubes 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.

[0486] 62. A fluid flow turbine blade assembly according to any one of embodiments 37-61, wherein the spacing between the deflector and the rotor blade is constant across the span of the deflector.

[0487] 63. A fluid flow turbine blade assembly according to any one of embodiments 37-61, wherein a spacing between the deflector and the rotor blade varies across at least a portion of the span of the deflector.

[0488] 64. A fluid flow turbine blade assembly according to any one of embodiments 37-63, wherein at least one of a radius of curvature and an arc length of the portion of the upstream surface having a concave shape varies along at least a portion of the span of the deflector.

[0489] 65. A fluid flow turbine blade assembly according to any one of embodiments 57-61, 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.

[0490] 66. The fluid flow turbine blade assembly of any one of embodiments 57, wherein the connector assembly comprises a variable angle connector assembly connecting the deflector to the rotor blade such that an angle of attack of the deflector relative to the rotor rotation plane is variable, the variable angle connector assembly comprising: a spar, the 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, the 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 a location where the second end of the spar is pivotally connected to the deflector; and a flexible shaft actuator, the flexible shaft actuator coupled to the first end of the flexible shaft to effect axial movement of the flexible shaft.

[0491] 67. A fluid flow turbine assembly as described in embodiment 66, wherein the flexible shaft actuator comprises: a guide tube assembly, the guide tube assembly being disposed within the rotor blade, the guide tube assembly comprising a guide tube housing having a guide bore in which a first end of the flexible shaft is supported and a guide tube movable within the guide bore, the first end of the flexible shaft being coupled to an end of the guide tube; a drive screw, the drive screw extending into a bore 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 a length of the drive screw, the threaded collar coupled to the guide tube such that axial movement of the collar is transmitted to the guide tube, causing axial movement of the guide tube within the guide bore, which in turn causes corresponding axial movement of the flexible shaft; and a motor, the motor coupled to the drive screw to provide powered rotation of the drive screw.

[0492] 68. A fluid flow turbine assembly as described in embodiment 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 for rotating the drive screw and in a second direction for rotating the drive shaft to transmit the rotation to a flexible shaft actuator of an adjacent variable angle connector assembly.

[0493] 69. A fluid-flow turbine blade assembly as described in any one of embodiments 37-68, wherein the deflector extends spanwise along the entire span of the rotor blade, including the root section and the working section.

[0494] 70. A fluid flow turbine blade assembly according to any one of embodiments 37-69, 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.

[0495] 71. A fluid flow turbine blade assembly according to any one of embodiments 37-70, wherein at least a portion of the trailing edge of the deflector includes a curved section of decreasing chord length between the leading edge of the deflector and the trailing edge of the deflector, the curved section extending to the tip of the deflector.

[0496] 72. A fluid flow turbine blade assembly as described in any one of embodiments 37-70, wherein at least a portion of the trailing edge of the deflector includes an arcuate section of increasing chord length between the leading edge of the deflector and the trailing edge of the deflector, the arcuate section extending to the tip of the deflector.

[0497] 73. A fluid flow turbine comprising: a hub; and a rotor comprising two or more than two of the turbine blade assemblies according to any one of embodiments 37-72 connected to the hub, the rotor rotatable about a rotor rotation axis, and each turbine blade assembly extending axially relative to the rotor rotation axis.

[0498] 74. A fluid flow turbine as described in embodiment 73, wherein the rotor rotation axis is oriented vertically or horizontally.

[0499] 75. A fluid flow turbine according to embodiment 73 or 74, comprising at least three of the turbine blade assemblies connected to a hub.

[0500] 76. A fluid flow turbine according to any one of embodiments 73-75, comprising a nacelle, wherein the hub is supported by or in the nacelle, and a tower supporting the nacelle.

[0501] 77. A fluid-flow turbine according to embodiment 76, further comprising at least one of a gearbox and a generator within the nacelle and operably coupled to the rotor.

[0502] 78. A fluid flow turbine according to embodiment 73, wherein at least a portion of the oncoming fluid flow is generally parallel to the rotor rotation axis.

[0503] 79. A hydro-driven turbine assembly comprising a fluid flow turbine according to any one of embodiments 73-78.

[0504] 80. A wind-driven turbine assembly comprising a fluid flow turbine according to any one of embodiments 73-78.

[0505] 81. A fluid flow turbine comprising: a hub; and a rotor comprising two or more than two of the turbine blade assemblies according to any one of embodiments 1-26 connected to the hub, the rotor rotatable about a rotor rotation axis, and each turbine blade assembly extending axially relative to the rotor rotation axis.

[0506] 82. A fluid flow turbine according to embodiment 81, wherein the rotor rotation axis is oriented vertically or horizontally.

[0507] 83. A fluid flow turbine according to embodiment 81 or 82, comprising at least three of the turbine blade assemblies connected to a hub.

[0508] 84. A fluid flow turbine according to any one of embodiments 81-83, comprising a nacelle, wherein the hub is supported by or in the nacelle, and a tower supporting the nacelle.

[0509] 85. A fluid-flow turbine according to embodiment 84, further comprising at least one of a gearbox and a generator within the nacelle and operably coupled to the rotor.

[0510] 86. A fluid flow turbine according to embodiment 81, wherein at least a portion of the oncoming fluid flow is generally parallel to the rotor rotation axis.

[0511] 87. A hydro-driven turbine assembly comprising a fluid flow turbine according to any one of embodiments 81-86.

[0512] 88. A wind-driven turbine assembly comprising a fluid flow turbine according to any one of embodiments 81-86.

[0513] 89 A fluid-flow turbine blade assembly, comprising: a rotor blade, the rotor blade comprising: a root section at which the rotor blade is attached to a hub of a fluid-flow turbine; a working section, the working section having a leading edge and a trailing edge, the working section configured and oriented to form a pressure surface facing an oncoming fluid flow impinging on the rotor blade and a suction surface; and a deflector, the deflector coupled to the rotor blade and extending spanwise along at least a portion of the working section of the rotor blade, the deflector having a leading edge, a trailing edge, and an upstream surface facing the oncoming fluid flow. a rotor blade having a front surface facing away from the oncoming fluid flow, the deflector configured such that when a fluid is flowing across the turbine blade assembly, the pressure on an area 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 exceeds the pressure over a similar area of ​​a rotor blade that does not have any deflector, and the suction on an area 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 exceeds the suction over a similar area of ​​a rotor blade that does not have any deflector.

[0514] 90. A fluid flow turbine blade assembly as described in embodiment 89, wherein the deflector has a substantially uniform thickness between the upstream surface and the downstream surface.

[0515] 91. A fluid flow turbine blade assembly as described in 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.

[0516] 92. A 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 the chord direction.

[0517] 93. A fluid flow turbine blade assembly as described in embodiment 92, wherein the portion of the upstream surface having the concave shape extends to the trailing edge of the deflector.

[0518] 94. A fluid-flow turbine blade assembly according to any one of embodiments 89-93, wherein the trailing edge of the deflector is mounted aft of the trailing edge of the working section relative to the direction of travel of the turbine blade assembly.

[0519] 95. A fluid flow turbine blade assembly according to any one of embodiments 89-94, wherein at least a portion of the 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 an upstream surface of the deflector and a downstream surface of the deflector.

[0520] 96. A 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.

[0521] 97. A 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 chord direction.

[0522] 98. A fluid flow turbine blade assembly as described in embodiment 97, wherein the portion of the upstream surface having a convex shape extends to the leading edge of the deflector.

[0523] 99. A fluid flow turbine blade assembly according to any one of embodiments 89-98, 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.

[0524] 100. A fluid flow turbine blade assembly as described in 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.

[0525] 101. A fluid flow turbine blade assembly according to any one of embodiments 89-100, wherein the leading edge of the deflector is mounted aft of the trailing edge of the working section relative to the direction of travel of the turbine blade assembly.

Claims

1. 1. A fluid flow turbine blade assembly comprising: a rotor blade comprising: a root section at which the rotor blade is attached to a hub of a fluid-flow turbine; and a working section, the working section having a leading edge and a trailing edge, the working section configured and oriented to define a pressure surface and a suction surface facing an oncoming fluid flow impinging on the rotor blade; a deflector coupled to the rotor blade and extending spanwise along at least a portion of the working section of the rotor blade, the deflector having 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, the deflector having a substantially uniform thickness between the upstream and downstream surfaces, at least a portion of the upstream surface along at least a portion of the span of the deflector having a concave shape in chordwise, the trailing edge of the deflector being mounted aft of the trailing edge of the working section relative to a direction of travel of the turbine blade assembly; A fluid flow turbine blade assembly comprising:

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

3. The fluid-flow turbine blade assembly of claim 1 or 2, wherein at least a portion of the upstream surface has a convex shape in the chord 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 a concave shape extends to the trailing edge of the deflector.

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

6. 6. The fluid-flow turbine blade assembly of claim 1, 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.

7. 7. The fluid-flow turbine blade assembly of claim 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.

8. 6. A fluid-flow turbine blade assembly according to claim 1, 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.

9. 9. The fluid-flow turbine blade assembly of claim 8, wherein along at least a portion of the span of the deflector, the trailing edge of the deflector is further from the oncoming fluid flow than the trailing edge of the rotor blade.

10. A fluid-flow turbine blade assembly according to any one of claims 1 to 9, wherein the leading edge of the deflector is mounted aft of the trailing edge of the working section relative to the direction of travel of the turbine blade assembly.

11. The fluid-flow turbine blade assembly of any preceding claim, further comprising a connector assembly connecting the deflector to the rotor blade.

12. The connector assembly includes: Tube and a deflector end flange fixedly connected to one end of the tube and to the deflector; a blade end flange fixedly connected to an opposite end of the tube and to the rotor blade; The fluid-flow turbine blade assembly of claim 11 , comprising:

13. 13. The fluid-flow turbine blade assembly of claim 12, wherein the turbine blade assembly is mounted 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, at least a portion of the oncoming fluid flow is parallel to the rotor axis of rotation, a first cross section of the tube defines an aerodynamic shape relative to the oncoming fluid flow that tapers toward a first leading edge of the first cross section and toward a first trailing edge of the first cross section, and a second cross section of the tube defines an aerodynamic shape relative to a fluid flow resulting from rotation of the rotor that tapers toward a second leading edge of the second cross section and toward a second trailing edge of the second cross section.

14. 14. The fluid-flow turbine blade assembly of claim 13, wherein the first cross-section is symmetrical about a line that bisects the first cross-section between the first leading edge and the first trailing edge, and the second cross-section is symmetrical about a line that bisects the second cross-section between the second leading edge and the second trailing edge.

15. 15. The fluid-flow turbine blade assembly of claim 12, comprising two or more connector assemblies, each positioned at a different spanwise position along the turbine blade assembly, the tube of each connector assembly being shaped between its opposing ends to follow an arc centered on an axis of rotation of the fluid-flow turbine and having a radius corresponding to the spanwise position of the connector assembly.

16. A fluid flow turbine blade assembly according to any preceding claim, 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 of any preceding claim, wherein the spacing between the deflector and the rotor blade varies across at least a portion of the span of the deflector.

18. 18. The fluid-flow turbine blade assembly of claim 1, 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.

19. 19. The fluid-flow turbine blade assembly of claim 1, wherein at least a portion of a chord extending between the leading edge of the deflector and the trailing edge of the deflector is positioned outside a profile of the deflector defined between the upstream surface of the deflector and the downstream surface of the deflector.

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

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

22. A fluid-flow turbine blade assembly according to any preceding claim, wherein the spanwise curvature of the leading edge of the deflector follows the spanwise curvature of the trailing edge of the blade.

23. 23. The fluid-flow turbine blade assembly of claim 1, further comprising one or more walls protruding from at least one of the upstream surface and the downstream surface of the deflector, each wall extending at least partially from the leading edge of the deflector to the trailing edge of the deflector.

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

25. 25. The fluid-flow turbine blade assembly of claim 1, wherein the deflector comprises two or more sections, each section connected to an adjacent section by a connector comprising top and bottom plates overlapping abutting ends of the section and the adjacent section, and fasteners extending through the top and bottom plates and portions of the section and the adjacent section where the top and bottom plates overlap.

26. 26. The fluid-flow turbine blade assembly according to claim 1, wherein the deflector has a cambered mean line, a center of curvature of a first portion of the cambered mean line being located on a downstream side of the deflector, and a center of curvature of a second portion of the cambered mean line being located on an upstream side of the deflector.

27. 27. A 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 a 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. 28. The fluid-flow turbine assembly of claim 27, wherein at a hub end of the deflector, at least one of the leading edge of the deflector and the trailing edge of the deflector is less proximate to the oncoming flow than at least one of the leading edge of the blade and the trailing edge of the blade.

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

30. 16. The fluid flow turbine blade assembly of claim 11, 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 connector assembly includes a variable angle connector assembly that connects the deflector to the rotor blades such that an angle of attack of the deflector relative to a rotor rotation plane is variable, the variable angle connector assembly comprising: 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 a location at which the second end of the spar is pivotally connected to the deflector; a flexible shaft actuator coupled to the first end of the flexible shaft to provide axial movement of the flexible shaft; The fluid-flow turbine blade assembly of claim 11 , comprising:

32. The flexible shaft actuator comprises: a guide tube assembly disposed within the rotor blade, the guide tube assembly comprising a guide tube housing having a guide hole in which the first end of the flexible shaft is supported and a guide tube movable within the guide hole, the first end of the flexible shaft being coupled to an end of the guide tube; a drive screw, the drive screw extending into a bore 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, the collar coupled to the guide tube such that the axial movement of the collar is transmitted to the guide tube, causing axial movement of the guide tube within the guide bore, which in turn causes corresponding axial movement of the flexible shaft; a motor coupled to the drive screw to provide motorized rotation of the drive screw; and The fluid-flow turbine assembly of claim 31 , comprising:

33. 33. The fluid-flow turbine assembly of 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 for rotating the drive screw and in a second direction for rotating the 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 preceding claim, wherein the deflector extends spanwise along the entire span of the rotor blade including the root section and the working section.

35. 35. The fluid flow turbine blade assembly of claim 1, wherein at least a portion of the trailing edge of the deflector includes a curved section of decreasing chord length between the leading edge of the deflector and the trailing edge of the deflector, the curved section extending to a tip of the deflector.

36. 35. A 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 of increasing chord length between the leading edge of the deflector and the trailing edge of the deflector, the arcuate section extending to a tip of the deflector.

37. 1. A fluid flow turbine blade assembly comprising: a rotor blade comprising: a root section at which the rotor blade is attached to a hub of a fluid-flow turbine; and a working section, the working section having a leading edge and a trailing edge, the working section configured and oriented to define a pressure surface and a suction surface facing an oncoming fluid flow impinging on the rotor blade; a deflector coupled to the rotor blade and extending spanwise along at least a portion of the working section of the rotor blade, the deflector having 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 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, 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 mounted aft of the trailing edge of the working section relative to a direction of travel of the turbine blade assembly; A fluid flow turbine blade assembly comprising:

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

39. 39. A 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 chord direction.

40. A 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. 40. The fluid flow turbine blade assembly of claim 39, wherein the portion of the upstream surface having a convex shape extends to the leading edge of the deflector.

42. 42. The fluid-flow turbine blade assembly of claim 37, 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. 43. The fluid-flow turbine blade assembly of 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. 42. A 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. 45. The fluid-flow turbine blade assembly of claim 44, wherein along at least a portion of the span of the deflector, the trailing edge of the deflector is further from the oncoming fluid flow than the trailing edge of the rotor blade.

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

47. 47. The fluid-flow turbine blade assembly of claim 37, wherein at least 25 to 90% of the chord extending between the leading edge of the deflector and the trailing edge of the deflector is positioned outside the profile of the deflector defined between the upstream surface of the deflector and the downstream surface of the deflector.

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

49. A 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. 50. The fluid-flow turbine blade assembly of claim 37, further comprising one or more walls protruding from at least one of the upstream surface and the downstream surface of the deflector, each wall extending at least partially from the leading edge of the deflector to the trailing edge of the deflector.

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

52. 52. The fluid-flow turbine blade assembly of claim 37, wherein the deflector comprises two or more sections, each section connected to an adjacent section by a connector comprising top and bottom plates overlapping abutting ends of the section and the adjacent section, and fasteners extending through the top and bottom plates and portions of the section and the adjacent section where the top and bottom plates overlap.

53. 53. The fluid-flow turbine blade assembly of claim 37, wherein the deflector has a cambered mean line, a center of curvature of a first portion of the cambered mean line being located on a downstream side of the deflector, and a center of curvature of a second portion of the cambered mean line being located on an upstream side of the deflector.

54. 54. A fluid-flow turbine assembly according to any one of claims 37 to 53, wherein along at least a portion of the span of the deflector extending to a 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.

55. 55. The fluid-flow turbine assembly of claim 54, wherein at a hub end of the deflector, at least one of the leading edge of the deflector and the trailing edge of the deflector is less proximate to the oncoming flow than at least one of the leading edge of the blade and the trailing edge of the blade.

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

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

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

59. 59. The fluid-flow turbine blade assembly of claim 58, wherein the turbine blade assembly is mounted to a hub of a rotor rotatable about a rotor axis of rotation, the turbine blade assembly being axially oriented relative to the rotor axis of rotation, at least a portion of the oncoming fluid flow being parallel to the rotor axis of rotation, a first cross section of the tube defining an aerodynamic shape relative to the oncoming fluid flow that tapers toward a first leading edge of the first cross section and toward a first trailing edge of the first cross section, and a second cross section of the tube defining an aerodynamic shape relative to a fluid flow resulting from rotation of the rotor that tapers toward a second leading edge of the second cross section and toward a second trailing edge of the second cross section.

60. 60. The fluid flow turbine blade assembly of claim 59, wherein the first cross section is symmetrical about a line that bisects the first cross section between the first leading edge and the first trailing edge, and the second cross section is symmetrical about a line that bisects the second cross section between the second leading edge and the second trailing edge.

61. 61. The fluid-flow turbine blade assembly of any one of claims 58 to 60, comprising two or more connector assemblies, each positioned at a different spanwise position along the turbine blade assembly, the tube of each connector assembly being shaped between its opposing ends to follow an arc centered on an axis of rotation of the fluid-flow turbine and having a radius corresponding to the spanwise position of the connector assembly.

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

63. A fluid flow turbine blade assembly according to any one of claims 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.

64. 64. A fluid-flow turbine blade assembly according to any one of claims 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.

65. 62. A fluid flow turbine blade assembly as claimed in 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 connector assembly includes a variable angle connector assembly that connects the deflector to the rotor blades such that an angle of attack of the deflector relative to a rotor rotation plane is variable, the variable angle connector assembly comprising: 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 a location at which the second end of the spar is pivotally connected to the deflector; a flexible shaft actuator coupled to the first end of the flexible shaft to provide axial movement of the flexible shaft; 58. A fluid flow turbine blade assembly according to any one of claims 57, comprising:

67. The flexible shaft actuator comprises: a guide tube assembly disposed within the rotor blade, the guide tube assembly comprising a guide tube housing having a guide hole in which the first end of the flexible shaft is supported and a guide tube movable within the guide hole, the first end of the flexible shaft being coupled to an end of the guide tube; a drive screw, the drive screw extending into a bore 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, the collar coupled to the guide tube such that the axial movement of the collar is transmitted to the guide tube, causing axial movement of the guide tube within the guide bore, which in turn causes corresponding axial movement of the flexible shaft; a motor coupled to the drive screw to provide motorized rotation of the drive screw; and 67. The fluid-flow turbine assembly of claim 66, comprising:

68. 68. The fluid-flow turbine assembly of 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 for rotating the drive screw and in a second direction for rotating the drive shaft to transmit rotation to a flexible shaft actuator of an adjacent variable angle connector assembly.

69. A 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. 70. A fluid flow turbine blade assembly according to any one of claims 37 to 69, 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.

71. 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 of decreasing chord length between the leading edge of the deflector and the trailing edge of the deflector, the curved section extending to a tip of the deflector.

72. 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 an arcuate section of increasing chord length between the leading edge of the deflector and the trailing edge of the deflector, the arcuate section extending to the tip of the deflector.

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

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

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

76. a nacelle, the hub being supported by or within the nacelle; a tower supporting the nacelle; A fluid flow turbine according to any one of claims 73 to 75, comprising:

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

78. 74. The fluid flow turbine of claim 73, wherein at least a portion of the oncoming fluid flow is generally parallel to the rotor axis of rotation.

79. A hydro-driven turbine assembly comprising a fluid flow turbine according to any one of claims 73 to 78.

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

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

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

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

84. a nacelle, the hub being supported by or within the nacelle; a tower supporting the nacelle; A fluid flow turbine according to any one of claims 81 to 83, comprising:

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

86. 82. The fluid flow turbine of claim 81 , wherein at least a portion of the oncoming fluid flow is generally parallel to the rotor axis of rotation.

87. A hydro-driven turbine assembly comprising a fluid flow turbine according to any one of claims 81 to 86.

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

89. 1. A fluid flow turbine blade assembly comprising: a rotor blade comprising: a root section at which the rotor blade is attached to a hub of a fluid-flow turbine; and a working section, the working section having a leading edge and a trailing edge, the working section configured and oriented to define a pressure surface and a suction surface facing an oncoming fluid flow impinging on the rotor blade; a deflector coupled to the rotor blade and extending spanwise along at least a portion of the working section of the rotor blade, the deflector having 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, the deflector configured such that when fluid is flowing across the turbine blade assembly, a pressure on an area 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 exceeds a pressure over a similar area of ​​the rotor blade without any deflector, and a suction on an area 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 exceeds a suction over a similar area of ​​the rotor blade without any deflector; A fluid flow turbine blade assembly comprising:

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

91. 90. The fluid flow turbine blade assembly of claim 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.

92. A fluid flow turbine blade assembly according to any one of claims 89 to 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 chord direction.

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

94. A fluid-flow turbine blade assembly according to any one of claims 89 to 93, wherein the trailing edge of the deflector is mounted aft of the trailing edge of the working section relative to a direction of travel of the turbine blade assembly.

95. 95. A fluid flow turbine blade assembly according to any one of claims 89 to 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 positioned outside a profile of the deflector defined between the upstream surface of the deflector and the downstream surface of the deflector.

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

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

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

99. 99. A fluid flow turbine blade assembly as claimed in 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. 100. The fluid-flow turbine blade assembly of 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 mounted aft of the trailing edge of the working section relative to the direction of travel of the turbine blade assembly.

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