1841results about "Engine manufacture" patented technology

A power turbine blade for a gas turbine engine includes at least one of a third-stage blade, a fourth-stage blade, or a fifth-stage blade. The power turbine blade includes a platform and an airfoil that extends in a spanwise direction from the platform to a tip shroud. The airfoil has an external airfoil surface formed in conformance with multiple cross-section airfoil profiles described by a set of Cartesian coordinates.

A cooled brush seal for use with a CMC component of a gas turbine engine having a hot side exposed to a hot gas path and an opposing side having a cavity for feeding a cooling flow to at least one film cooling hole. The cooled brush seal includes: an OD backing plate; an ID backing plate; a plurality of brush seal bristles sandwiched between the OD backing plate and the ID backing plate; a first hole extending through the OD backing plate, the brush seal bristles, and the ID backing plate; and a cover plate attached to an inner surface of the ID backing plate and including a second hole circumferentially offset from the first hole and forming a second passage into the cavity, wherein the ID backing plate and the cover plate form a circumferential cooling passage extending between the first hole and the second hole.

A fan assembly has a substantially centrifugal outlet, an axial intake, an airflow channel extending substantially perpendicular to the axial intake, and a guide element for redirecting airflow adjacent the axial intake. The axial intake is spaced apart from a back wall of the airflow channel by a first distance, and the guide element is positioned between the axial intake and the back wall of the airflow channel, or the guide element comprises a back surface of the fan assembly. The airflow from the airflow channel then passes through the guide element to enter the axial intake.

Systems and methods are provided for assembling and installing multiple wind turbines from a single vessel. In general, different embodiments use wind turbine components on the vessel including blades, a nacelle assembly with a rotating hub, and a tower. A Turbine Installation Gantry System (TIGS) embodiment uses a gantry system with a truss substructure and at least one bridge crane on an elevated vessel for assembling the wind turbine blades on the vessel to a nacelle hub supported on the seabed. A Skidding Turbine Installation Crane (STIC) embodiment has a rotatable crane mounted on a skidding pedestal or cantilever structure, providing full access to the vessel deck and blades, and for bringing the assembled nacelle assembly outboard to assemble each blade. A Turbine Assembly Positioning System (TAPS) embodiment includes both a handling system and a crane mounted on a skidding cantilever structure for securing the blades to the assembled tower section and nacelle hub that are cantilevered outboard of the vessel by the handling system. The combination embodiment uses selected components and systems from the TIGS, STIC and TAPS embodiments to provide component and system redundancy and concurrent operation.

The present disclosure relates to methods (40) and assemblies for installing a bushing (50) in a root (16) of a wind turbine blade (10). The present disclosure further relates to methods (40) and assemblies for replacing a bushing of a wind turbine blade (10). A method (40) comprises providing (41) a bushing hole (51); inserting (42) a bushing (50) wrapped in a reinforcement fabric (52) in the hole (51), the bushing (50) being closed at a tip end portion. The method (40) further comprises creating (43) vacuum in the hole (51), infusing (44) the reinforcement fabric (52) with resin, and curing the resin.

A cooling flow arrangement for a ceramic matrix composite (CMC) component of a turbine engine, wherein the CMC component includes a hot side configured for exposure to a hot gas path of the turbine engine and an opposing cold side. At least one cavity is provided in the CMC component, the at least one cavity having an entrance disposed on the cold side that is configured for receiving a cooling flow. A seal is disposed adjacent the at least one cavity and the cold side of the CMC component and is configured to provide a seal between the CMC component and an upstream turbine component. At least one hole extends through the seal and is positioned to provide the cooling flow to the at least one cavity of the CMC component.

A reusable upper stage rocket or other atmospheric re-entry vehicle includes a nose, a base opposite the nose, and a propulsion engine toward the base. The propulsion engine includes a high pressure chamber and a nozzle configured to exhaust gas generated by the high pressure chamber. The nozzle includes an initial nozzle portion, a secondary nozzle portion downstream of the initial nozzle portion, and a nozzle exit at a downstream end of the secondary nozzle portion. The secondary nozzle portion includes an inner expansion surface, an outer expansion surface outboard of the inner expansion surface, and an expansion cavity defined between the inner expansion surface and the outer expansion surface.

In a first aspect of the present invention there is provided a method of repowering a horizontal-axis wind turbine comprising a tower, a nacelle located rotatably at the apex of the tower, and a rotor having a hub and at least three used blades mounted pitchably to the hub and extending radially therefrom, the method comprising the steps of uninstall the at least three used blades from the hub, install at least three repower blades to the hub, each repower blade extending between a root and a tip, and each repower blade further comprising a connection point located between the root and the tip, install a plurality of blade connecting members, each blade connecting member being connected between corresponding connection points of a pair of repower blades; and install a tensioning system with the hub, the tensioning system being configured to adjust a tension in each blade connecting member.

An electric submersible pump stage optimized for viscous fluid is provided. The stage can include a diffuser having a curved break water area. The stage can include an impeller having a cut back shroud and / or hub.

A method of overhaul is provided. During this overhaul method, a substrate is scanned using structured light to provide substrate scan data. The substrate is from a component previously installed within an engine. The substrate scan data is compared to substrate reference data to provide additive manufacturing data. Material is deposited with the substrate using an additive manufacturing device based on the substrate scan data to provide a first object. The first object is scanned using the structured light to provide first object scan data. The first object scan data is compared to first object reference data to provide machining data. The first object is machined using the machining data.

A method of transporting a first vessel having wind turbine components to an offshore installation vessel. The method includes (i) securing the first vessel to a second vessel using a first tow line attached to a front end (or bow) of the first vessel, and (ii) securing the first vessel to a third vessel using a second tow line attached to a back end (or stern) of the first vessel. The method further includes transporting the first vessel to the offshore installation vessel using the second vessel and the third vessel secured to the first vessel via the first and second tow lines, respectively. The method also includes securing the first vessel to the offshore installation vessel. The first vessel can include one or more fender walls. The first vessel can be secured to the offshore installation vessel using one or more mooring lines.

A blade noise reduction device, comprising a plurality of sawtooth units. The plurality of sawtooth units are arranged in a first direction. Each sawtooth unit comprises secondary teeth and a primary tooth, which extend in a second direction, wherein at least one secondary tooth is distributed on each of two sides of the primary tooth, the tooth vertex angle of the secondary tooth being smaller than the tooth vertex angle of the primary tooth. The blade noise reduction device can remarkably improve the noise reduction effect. In addition, the present invention further relates to a blade having the blade noise reduction device, and a wind turbine generator set having the blade.

According to the present invention there is provided a method of assembling a modular wind turbine blade comprising first and second blade modules connectable together at an interface to form at least part of the modular wind turbine blade. The method comprises providing a first blade module and a second blade module. Each blade module comprises an outer shell defining an outer surface of the blade module, a connecting region of the outer shell defining an interface end of the blade module, and a longitudinally-extending spar cap embedded in the outer shell. The spar cap has a tapered end portion in the connecting region in which the thickness of the spar cap decreases towards the interface end of the blade module such that a tapered recess is defined in the outer surface of the blade module. The method further comprises arranging the first and second blade modules end-to-end with the tapered recesses aligned to define a bridge recess. The tapered recess of the first blade module defines a first end of the bridge recess, and the tapered recess of the second blade module defines a second end of the bridge recess. The method further comprises arranging a stack of layers in the bridge recess and spanning the interface between the first and second blade modules. The stack of layers comprises a plurality of pre-cured layers interleaved with pre-preg interlayers. The pre-preg interlayers comprise fibrous material that is pre-impregnated with uncured resin. The method further comprises applying heat to the stack of layers in the bridge recess such that the resin in the pre-preg interlayers mobilises in the bridge recess. The method further comprises curing the resin to integrate the pre-cured layers with each other to form a spar bridge spanning the interface, the spar bridge serving to connect the spar caps of the first and second blade modules.

An aircraft system is provided that includes a propulsor rotor, an electric machine and a gas turbine engine. The electric machine is operatively coupled to and configured to drive rotation of the propulsor rotor. The gas turbine engine is operatively coupled to and configured to drive rotation of the propulsor rotor. The gas turbine engine includes a compressor section, a combustor section, a turbine section, an exhaust duct and a flowpath extending through the compressor section, the combustor section, the turbine section and the exhaust duct. The exhaust duct extends longitudinally along the electric machine. The exhaust duct extends partially circumferentially about the electric machine between opposing circumferential sides of the exhaust duct.

Described is a device for offshore arranging of a wind turbine or components thereof on a foundation present at sea. The device includes an elongate superstructure connected releasably to the foundation and extending between a lower surface and an upper surface thereof in the vertical direction from the foundation. The superstructure has an internal space which is accessible to a tower section of the wind turbine and in which the tower section can be received. Further present is a horizontally displaceable supply structure for a tower section. The supply structure is configured to move a tower section coupled thereto from outside the internal space into the internal space by a horizontal displacement. An engaging structure, received for vertical displacement in the internal space, is configured to lift an engaged tower section in the internal space by a vertical displacement, whereby sufficient space is created under the relevant tower section for receiving another, underlying tower section in the internal space.

A fuel system for a hydrogen-fueled gas turbine engine includes a main fuel conduit configured to conduct hydrogen fuel from a hydrogen storage unit to a core combustor of the gas turbine engine, a pre-heater including an auxiliary combustor configured to combust hydrogen fuel diverted from the main fuel conduit to heat hydrogen fuel in the main fuel conduit. A first exhaust passage is configured to conduct combustion products from the auxiliary combustor to the core combustor of the gas turbine engine.

The systems and methods for assembling and installing multiple wind turbines from a single vessel tire provided. Generally, the different embodiments use wind turbine components on the vessel that include blades, a nacelle assembly having a rotating hub, and a tower. A Turbine Installation Gantry System (T.I.G.S.) embodiment uses a gantry system having a truss sub-structure and at least one bridge crane on the elevated vessel for assembling the wind turbine blades on board to the nacelle hub supported above the seabed. A Skidding Turbine Installation Crane (S.T.LC.) embodiment has a rotatable crane mounted on a skidding pedestal or cantilever structure to provide full access to the vessel deck and the blades outboard of the vessel for assembling each of the blades with the assembled nacelle assembly outboard. A Turbine Assembly and Positioning System (T.A.P.S.) embodiment includes a handling system and a crane both mounted onto a skidding cantilever structure for fastening blades to an assembled tower section and nacelle hub suspended cantilevered outboard of the vessel by the handling system. A combination embodiment uses selected components and systems from the T.I.G.S., S.T.LC, and T.A.P.S. embodiments to provide redundancy and simultaneous movements of components and systems.

A turbine exhaust duct (TED) for an aircraft engine, has: a body having a central axis and having an inner wall and an outer wall conjointly defining an annular inlet conduit and outlet conduits communicating with the annular inlet conduit and extending generally radially outward relative to the annular inlet conduit along conduit axes extending transversally to the central axis, the body defining a central passage located radially inwardly of the annular inlet conduit, the outlet conduits having transition areas transitioning from a mainly axial direction to a mainly radial direction; and stiffeners secured to the body and located within the central passage at circumferential positions being in register with the outlet conduits, the stiffeners secured to the transition areas of the outlet conduits, the stiffener extending transversally to both of the central axis and the conduit axes.

The present invention relates to a valve arrangement. The present invention further relates to a fluid flow control element. Furthermore, the present invention relates to a turbomachine system comprising such a valve arrangement and / or fluid flow control element. Moreover, the present invention relates to a method and a use relating to the valve arrangement and / or the fluid flow control element.

There is provided a fluid flow machine (10) comprising: a casing structure (24), a turbomachine blade (311) disposed within the casing structure (24), and a sealing arrangement (330) coupled to the casing structure (24). The sealing arrangement comprises (330) an abrasion portion (334) including a lattice structure (400). The abrasion portion (334) is configured to provide a seal with a tip (321) of the turbomachine blade (311). There is also provided a method (600) of manufacturing such a fluid flow machine (10).

An assembly is provided for a turbine engine (20). This assembly includes a carrier (80), a control ring (82) and a bladed outer air seal (78) mounted to the carrier (80). The carrier (80) extends circumferentially around an axis (22). The carrier (80) includes an annular cavity (114), a first section (106) and a second section (108). The annular cavity (114) is formed within the carrier (80) by the first section (106) and the second section (108). The first section (106) is welded and / or brazed to the second section (108) at a sealed full-hoop bond joint (148; 150). The first section (106) is further connected to the second section (108) at a second sealed full-hoop joint (148; 150). The control ring (82) extends circumferentially around the axis (22) within the annular cavity (114). A method of manufacture is provided for an assembly for a turbine engine (20).

The present invention relates to a propeller (10) for a blowing device, configured to be driven in rotation about a longitudinal axis (A), the propeller comprising: - a proximal wall (4) defining an inlet opening (40) admitting an airflow directed along the longitudinal axis (A), - a plurality of air passage channels (3) in fluidic communication with the inlet opening (40), said air passage channels (3) being positioned around the longitudinal axis (A), each air passage channel (3) extending radially between an inlet end and an outlet end, the outlet end having an outlet cross-section (34) having a maximum dimension parallel to the longitudinal axis (A) greater than or equal to 4 millimeters. The present invention further relates to a blowing device, preferably a hair dryer or a vacuum cleaner, comprising such a propeller.

A fan assembly comprising an airflow generator and a nozzle. The nozzle comprising a body defining an air inlet to receive generated airflow, an air outlet section, and a switching member. The switching member switches between a first position, delivering only a first airflow to the outlet, and a second position, delivering both first and second airflows. The air outlet section comprises a first inlet for the first airflow, a second inlet for the second airflow, an air outlet for emitting airflow from the fan assembly, and pathways between the first inlet and the air outlet. In the first position, the first airflow travels along the first pathway and is emitted in a first outlet direction. In the second position, the second airflow interacts with the first, redirecting it along the second pathway, and emitting it in a second, different outlet direction.

A radial inlet body of a gas turbine engine compressor is provided. The radial inlet body includes plenums arranged around opposite sides of an inlet portion defining a compressor inlet. The plenums include outer surfaces with increasing radii of curvature and a flow diverter. The flow diverter is disposed aside the inlet portion opposite a duct. The plenums are configured to direct flows from the duct around the inlet portion. The flow diverter and the plenums are configured to cooperatively encourage uniform distribution of the flows. The flow diverter includes curvilinear sides that tangentially register with and smoothly lead to the outer surfaces of the plenums and a cusp where the curvilinear sides meet. The radial inlet body further includes a front sidewall supporting the inlet portion and an aft sidewall opposite the front sidewall. The front and aft sidewalls are angled toward one another along the plenums.

The present disclosure may be embodied as a blade for a wind turbine. The blade includes a spar and a blade body arranged around the spar. The blade may include a root, a tip, and one or more body sections, each body section having a length, a stiffness ratio. The blade may further include two or more boundary actuators, each boundary actuator positioned at a boundary end of a body section, wherein each boundary actuator is configured to engage the corresponding boundary end to twist the body section. The length and stiffness ratio of each section may be optimized for maximum efficiency during Region 2 operation.

A cooking appliance comprising a first fan (1) arranged to produce an air flow in a cooking chamber (51) and a motor (2), whereinthe first fan (1) comprises: a shaft connection part (11) connected to a motor shaft of the motor; a hub (12) coaxially connected to the shaft connection part (11), a first air inlet (1221) being provided at an end of the hub (12) away from the motor (2); and a plurality of blades (13) connected to the hub (12) and arranged at intervals in a circumferential direction of the hub (12), a first air outlet (1211) being defined between the hub (12) and any two adjacent blades (13), circumscribed circles of the plurality of blades (13) having a diameter that gradually increases in a direction approaching the motor (2).

An assembly of a gas turbine engine, having: a shaft having a shaft outer surface and a shaft inner surface, the shaft axially extends from a shaft forward end to a shaft aft end, the shaft forward end defines axially extending shaft slots that are circumferentially spaced apart from each other; a bearing having a first race, the first race is ring shaped with a first race outer surface and a first race inner surface, the first race is sized so the first race inner surface fits around the shaft outer surface, the first race extends axially from a first race forward end to a first race aft end, the first race forward end defines radially inwardly extending bosses that are circumferentially spaced apart from each other and aligned with ones of the axially extending slots of the shaft forward end, rotationally fixing the first race against the shaft.

Offset crimp insert and its crimping method An aspect of the invention relates to an offset insert (3) to be crimped into a composite turbomachine element comprising on the one hand a head (31) comprising an internal surface (310), an external surface (311) opposite the internal surface (310), an external peripheral edge (313) connecting the internal surface (310) to the external surface (311), and on the other hand a cylindrical shaft (32) along a central axis (y), extending from the internal surface (310) of the head (31) in an axial direction to an external axial end (321). The insert further comprises a fixing hole (30) centered along an adjustment axis (x) parallel to the central axis (y) extending from the outer surface (311) to the outer axial end (321) of the shaft (32), characterized in that the adjustment axis (x) of the fixing hole (30) is offset by at least 1 mm with respect to the central axis (y) of the shaft (32). Figure to be published with the abbreviation: Figure 3d

A rear portion of a turbojet engine with converging-diverging nozzles includes a device for controlling the position of the diverging vane relative to the position of the converging vane, the device including a first link (120) having a first end (120A) hinged to the converging vane (30) and an opposite second end (120B), a second link (122) having a first end (122A) hinged to the diverging vane (32) and an opposite second end (122B), and a third link (124) having a first end (124A) hinged to a synchronization ring (82) and an opposite second end (124B). The second end (120B) of the first link is hinged to the second end (122B) of the second link and / or to the second end (124B) of the third link, and the second end (124B) of the third link (124) is hinged to the second end (122B) of the second link (122).

An arrangement is for use in any of installing or replacing a part, maintaining, and constructing a wind turbine, the arrangement having a longitudinal structure at least partially supported on a wind turbine tower, a guide track connected to the longitudinal structure and a dolly arranged to follow the guide track along the longitudinal structure.