Abstract: An arrangement with a nacelle and a radiator arrangement of a wind turbine is provided. The radiator arrangement includes a guiding assembly. The nacelle includes a guiding assembly, too. The guiding assembly of the radiator is positioned and constructed in a way that the guiding assembly interacts with the guiding assembly of the nacelle. Thus, the radiator arrangement is lifted and passed to a final position on top of the nacelle by the engaged guiding assemblies.

Abstract: The pattern has a pattern material and a casting core combination. The pattern material has an airfoil. The casting core combination is at least partially embedded in the pattern material. The casting core combination comprises a metallic casting core and at least one additional casting core. The metallic casting core has opposite first and second faces. The metallic core and at least one additional casting core extend spanwise into the airfoil of the pattern material. In at least a portion of the pattern material outside the airfoil of the pattern material, the metallic casting core is bent transverse to the spanwise direction so as to at least partially surround an adjacent portion of the at least one additional casting core.

Abstract: The method for de-icing composite material structures, particularly blades of a wind turbine made from composite materials, includes the following steps: disposing at least one layer of a formulation of conductive polymer on at least one portion of the surface of the structure, providing an appropriate electrical power supply for the structure, and connecting the layer of a formulation of conductive polymer to the electrical power supply in such a way as to cause the conductive layer of conductive polymer to heat up, controlling the electrical power supply depending on climatic conditions. The required composition and suitable device are also described. A specific application is the blades of wind turbines.

Abstract: A wind turbine rotor blade includes: a rotor blade root; a rotor blade tip; an electrical heating device; a first lightning receptor disposed in the region of the rotor blade tip; precisely two lightning conductors leading from the lightning receptor to the rotor blade root; a second lightning receptor arranged at a distance to the rotor blade tip and connected to one of the lightning conductors; and, each one of the two lightning conductors being electrically conductively connected to the electrical heating device at a multiplicity of points between the rotor blade root and the rotor blade tip so as to cause equipotential bonding between the two lightning conductors via the electrical heating device in response to a lightning strike to the rotor blade.

Abstract: A process of preparing a turbine rotor wheel, a repair tool for machining a turbine rotor wheel, and a turbine rotor wheel are disclosed. The process includes providing the turbine rotor wheel, the turbine rotor wheel having a dovetail slot, a cooling slot, and a dovetail acute corner formed by the dovetail slot and the cooling slot and removing a stress region from the dovetail acute corner. The repair tool permits removal of strained material while also reducing the operating stress of the feature. The turbine rotor wheel includes a machined portion resulting in lower stress for the turbine rotor wheel.

Abstract: A heat shield for a rotor in a turbine engine is provided. The heat shield includes a main body having a first pair of recesses. The first pair of recesses is adapted to fit around a portion of one or more rotor blades or between two axially adjacent rotor wheels. The first pair of recesses limits axial and radial movement of the heat shield by interaction with the rotor blades or by interaction with the two axially adjacent rotor wheels. The first pair of recesses engage axially adjacent rotor blades or the axially adjacent rotor wheels. The heat shield protects the rotor from hot gas.

Abstract: A compressor that includes a frame, a rotor assembly, and a heat sink assembly. The rotor assembly includes a bearing assembly to which the heat sink assembly is secured. The compressor is configured such that, during use, air is drawn through the interior of the frame. The heat sink assembly then extends radially from the bearing assembly into the air path through the frame such that the air flows over the heat sink assembly.

Abstract: A compressor that includes a frame, a rotor assembly, and a heat sink assembly. The rotor assembly includes a shaft to which an impeller, a bearing assembly and a rotor core are secured. The heat sink assembly is then secured to the bearing assembly and to the frame.

Abstract: An impeller may include a hub section, a plurality of blades, and a shroud. The hub section may be mounted on a rotatable shaft. The hub section may define a central opening for the rotatable shaft to extend therethrough and may define a plurality of holes disposed in a circular manner about the central opening. The plurality of blades may be connected to or integral with the hub section. The shroud may be connected to or integral with the hub section and the plurality of blades. The plurality of holes may be either through holes or partially drilled holes. A bottom of some or all of the partially drilled holes may be flat, conical, or rounded. Some or all of the partially drilled holes may have one or more bleed holes that may permit quenching material to flow therethrough and prevent the quenching material from stagnating therein.

Abstract: A gas turbine engine is disclosed having a thermoelectric device capable of changing a tip clearance in a turbomachinery component. In one non-limiting form the turbomachinery component is a compressor. The thermoelectric device can be used in some forms to harvest power derived from a waste heat. The tip clearance control system can include a sensor used to determine a clearance between a tip and a wall of the turbomachinery component.

Abstract: A gas turbine engine is disclosed having a thermoelectric device capable of changing a tip clearance in a turbomachinery component. In one non-limiting form the turbomachinery component is a compressor. The thermoelectric device can be used in some forms to harvest power derived from a waste heat. The tip clearance control system can include a sensor used to determine a clearance between a tip and a wall of the turbomachinery component.

Abstract: Provided is a wind power generation system that is less likely to change its cooling performance depending on the wind direction. In order to solve the above problem, the wind power generation system of the invention includes blades adapted to rotate upon receiving wind, a generator for performing a power generating operation by rotating a rotor together with rotation of the blades, a nacelle for supporting the blades via a main shaft, a tower for rotatably supporting the nacelle, a power conditioning system or transformer accommodated in the tower, and a plurality of radiators disposed on an outer peripheral side of the tower for cooling the power conditioning system or the transformer. The radiators positioned substantially at the same height are arranged at substantially equal intervals in a circumferential direction of the tower.

Abstract: A turbine rotor assembly (32) comprising a turbine rotor (34) and a plurality of circumferentially spaced radially outwardly extending turbine rotor blades (36). The turbine rotor (34) has a rim (38) and a plurality of circumferentially spaced slots (40) provided in the rim (38) of the turbine rotor (34). Each turbine rotor blade (36) has a root (42) and the root (42) of each turbine rotor blade (36) is arranged in a corresponding one of the slots (40) in the rim (38) of the turbine rotor (34). Each of the slots (40) has a chocking device (50) and each chocking device (50) abuts a radially inner surface (52) of the slot (40) and each chocking device (50) abuts a radially inner surface (48) of the root (42) of the corresponding turbine rotor blade (36).

Abstract: The gas turbine engine (S1) includes: turbine blades (7b); and a cooling air supply unit (11) to supply cooling air to the turbine blades (7b). A flow path surface (31) is formed so as to be positioned in an upstream side of the turbine blades (7b) and so as to be connected to a base surface (32) in which the turbine blades (7b) are provided. The flow path surface (31) includes: depression portions (31a) depressed relative to the base surface (32), each depression portion (31a) including at least an area overlapping with a front end (7b1) of each turbine blade (7b), when viewed from a direction of the turbine axis (L); and protrusion portions (31b) protruding relative to the base surface (32), each protrusion portion (31b) being at least part of each area positioned between front ends (7b1) of the turbine blades (7b), when viewed from the above direction.

Abstract: An assembly includes a gas turbine engine component and a plate. The plate is spaced from a surface of the component and generally conforms to the shape of the surface. The plate and component form a passageway that allows for passage of a secondary gas flow between the component and the plate.

Abstract: It has a flat impingement hole (2) of which the opening width (D1) in the flow direction of a crossflow (F) in the gap between a cooling target (10) and an opposing member (20) is set greater than the opening width (D2) in a direction orthogonal with the flow direction of the crossflow F. Accordingly, the cooling efficiency is further improved by the impingement cooling mechanism.

Abstract: A coated substrate with a subsurface cooling channel having no corner disposed proximate a seam between the substrate and the coating. A method for forming such a structure, including forming a groove in a surface of a substrate, forming a preform having a cooperating portion and a protruding portion, inserting the cooperating portion of the preform into the groove, leaving the protruding portion of the preform protruding beyond the surface of the substrate, applying a layer of a coating material to the surface of the substrate and the protruding portion of the perform, and removing the preform, thereby creating a cooling channel.

Abstract: A radiator arrangement is arranged on a nacelle of a wind turbine via a sliding arrangement. The sliding arrangement is constructed and arranged in a way that the radiator arrangement is allowed to change its position in reference to the nacelle between a first position and a second position. The radiator arrangement allows service from inside the nacelle if the radiator arrangement is the first position and the radiator arrangement transfers heat in its second position.

Abstract: A cooling arrangement is provided for a turbine disc of a gas turbine engine. The turbine disc has a plurality of circumferentially spaced disc posts forming fixtures therebetween for a row of turbine blades. Each turbine blade has an attachment formation which engages at a respective fixture, a platform radially outwardly of the attachment formation such that the adjacent platforms of the row form an inner endwall for the working gas annulus of the engine, and an aerofoil which extends radially outwardly from the platform. A respective cavity is formed between an exposed radially outer surface of each disc post and the inner endwall. The cooling arrangement has at each disc post, a cooling plate located in the respective cavity and spaced radially outwardly from the exposed outer surface of the disc post to form a cooling channel between the cooling plate and the exposed outer surface.

Abstract: An energy collection system may collect and use the energy generated by an electric field. Collection fibers are suspended from a support wire system supported by poles. The support wire system is electrically connected to a load by a connecting wire. The collection fibers may be made of any conducting material, but carbon and graphite are preferred. Diodes may be used to restrict the backflow or loss of energy.

Abstract: A heli-hoist pad (18) that is incorporated into a wind turbine nacelle (12) in a manner that is optimized for helicopter approach and positioning of the heli-hoist pad (18), such as by being located within a recess (20) in an upper surface (28) of the wind turbine nacelle (12). Heat exchangers (50) may also be positioned within the free flow of wind outside of a nacelle (12) in manners that provide for serviceability while also allowing for optimal positioning of a heli-hoist pad (18).

Abstract: A propeller assembly comprises two or more blade elements each comprising two or more blade element portions arranged sequentially radially along the blade element. Each of the two or more blade element portions that are radially equi-positioned along corresponding ones of the two or more blade elements together form a blade element portion array. Each of the two or more blade element portions comprise at least one heating element with each one of the at least one heating elements that is located in a correspondingly radially positioned blade element portion being connected to one another to form a heating element array. The two or more heating element arrays are adapted to sequentially heat respective ones of the two or more blade element portion arrays so as to de-ice the blade elements.

Abstract: A hollow blade for a turbomachine comprises an airfoil portion; the airfoil portion extends longitudinally for a length; the airfoil portion is defined laterally by an external surface; the airfoil portion has at least one internal cavity extending along said length and defined laterally by an internal surface; the airfoil portion has a set of channels extending from the external surface to the internal surface; the openings of said channels on said external surface are aligned along a curved line that reflects an isobar on said external surface.

Abstract: A de-icing arrangement of a wind turbine rotor blade is provided. The de-icing arrangement includes an electrically conductive mat, an electrically conductive band for distributing an electric current along a first edge of the mat, and a current supply connector for connecting the band to a current supply, wherein at least the electrically conductive mat is embedded in the body of the rotor blade. A wind turbine including a number of rotor blades including such a de-icing arrangement according, and a current supply for connecting to the de-icing arrangements of a rotor blades. A method of incorporating a de-icing arrangement in a wind turbine rotor blade is also provided.

Abstract: A gas turbine engine, a rotor assembly for a gas turbine engine, and a method for thermally insulating an impeller in a gas turbine engine are provided. In one embodiment, the gas turbine engine includes an impeller having a front face configured to modify a direction of air flow through the gas turbine engine. The impeller further includes backface to which a heat shield is mounted. A closed cavity is defined between the heat shield and the backface of the impeller, and is configured to insulate the backface of the impeller from a high temperature environment.

Abstract: A propeller system for an aircraft includes a propeller assembly rotatable about a central axis and a reduction gearbox operably connected to the propeller assembly via a propeller shaft. An electrical power transfer system is positioned such that the gearbox is located axially between the electrical power transfer system and the propeller assembly. The electrical power transfer system includes a slip ring assembly secured to an oil transfer tube extending to the propeller assembly and a brush block interactive with the slip ring assembly to transfer electrical power to a plurality of lead wires extending from the slip ring assembly to the propeller assembly. The brush block is positioned such that brush block tips of the brush block extend toward the slip ring assembly in a substantially radial direction relative to the central axis of the propeller assembly.

Abstract: A blade retainer for a gas turbine engine includes a plate-like member with an arcuate outer face, an opposed inner face, and two spaced-apart end faces. The member has an outer portion disposed adjacent the outer face, and an inner portion disposed adjacent the inner face, and a wedge-shaped recess with a concave radiused valley is formed in the inner portion adjacent each end face. The retainer is left-right symmetrical.

Abstract: A turbine nozzle having a non-linear cooling conduit is disclosed. In one embodiment, a turbine nozzle includes: an airfoil, at least one endwall adjacent the airfoil, and a fillet region connecting the airfoil and the at least one endwall, the fillet region including an outer surface. The turbine nozzle also includes a non-linear cooling conduit located within the fillet region and adjacent the outer surface of the fillet region, the non-linear cooling conduit allows fluid flow through the fillet region. The non-linear cooling conduit spans substantially along an axial length of the airfoil between a leading edge of the airfoil and a trailing edge of the airfoil. Additionally, the non-linear cooling conduit includes an arc profile substantially similar to an arc profile of the airfoil.

Abstract: A wind turbine component (18) includes an inner member (32) and an outer member (34) disposed relative to the inner member (32), wherein the inner and outer members (32, 34) move relative to each other. A plain bearing (200) is coupled to one of the inner or outer member (32, 34) and configured to provide a fluid film (202) for maintaining separation of and facilitating relative movement between the inner and outer members (32, 34). A position adjustment mechanism (78) is coupled to the one of the inner or outer member (32, 34) for selectively moving the plain bearing (200). A position controller (176) may be operatively coupled to the position adjustment mechanism (78) for controlling the position of the plain bearing (200). The wind turbine component may be a wind turbine generator (18) with the inner member and outer member corresponding to one of the stator and rotor assemblies (32, 34). Methods for controlling the generator are also disclosed.

Abstract: A method and system for enhancing the heat transfer of turbine engine components is disclosed that includes applying a metallic coating having a high thermal conductivity to the cold side of a turbine component to enhance heat transfer away from the component. The metallic coating may be roughened to improve heat transfer. The metal coating may be a Ni—Al bond coating having an aluminum content greater than about 50 weight percent.

Abstract: The present invention relates to an improvement of windmill rotors—more specifically rotors that have been designed to be used in cold and wet climate, such as northern sea areas. This can be achieved by incorporating an electrically conducting layer on or in the surface of a windmill blade. The same coating can also be used to achieve a stealth property.

Abstract: A turbine engine includes a turbine, a compressor for compressing air and a combustor for receiving the compressed air through an inlet passage and operable to burn fuel therewith to deliver hot exhaust gas to the turbine. Also included is a wheel space defined proximate to the combustor. Further included is a cooling air passage extending between the compressor and the wheel space. Yet further included is a valve assembly having a valve member disposed in the cooling air passage and operable to admit a cooling air to the wheel space in response to a condition therein.

Abstract: A damper for a turbine rotor assembly of a gas turbine engine may include a forward plate with a forward face and an aft face, and an aft plate with a forward face and an aft face. The aft face of the forward plate may be connected to the forward face of the aft plate with a longitudinal structure. An area of the aft plate in a plane transverse to the longitudinal structure may be greater than an area of the forward plate in the plane transverse to the longitudinal structure. The damper may also include a pocket on the forward face of the forward plate.

Abstract: A cover plate for use with a rotor disk in a gas turbine engine includes an enclosed chamber associated with a web on the rotor disk. The enclosed chamber ensures that adequate cooling air is delivered by rotation of the cover plate.

Abstract: The disclosure relates to a radially fed axial steam turbine with a cold inlet duct, axially displaced from a hot inlet duct such that is it further away from a first blade row than the hot inlet duct. The cold inlet duct receives a cold steam from a cold inlet spiral and directs it into the hot inlet duct in such a way that a boundary layer of cold steam is formed over the rotor circumferential surface between the outlet end of the cold inlet duct and the blade and vane rows. The rotor circumferential surface is also adapted to promote and maintain the boundary layer. In this way, a maximum temperature to which the rotor is exposed can be reduced.

Abstract: A fish mouth seal carrier for a guide vane arrangement of a gas turbine comprises a first half-shell element and a second half-shell element bonded to it, which together form a box profile with two axial arms and two radial arms. A sealing element is arranged on one of the axial arms of the box profile. At least one of the two half-shell elements has an integrally formed axial flange for forming, with a guide vane platform, a fish mouth seal accommodating an axial flange of an adjoining moving blade radially between the guide vane platform and the axial flange of the seal carrier.

Abstract: A wind turbine generating apparatus includes a rotor head that rotates upon receiving outside wind on a wind turbine blade, a generator that generates electricity, and a nacelle interior air passage through which outside air flows isolatedly from an interior space of the nacelle.

Abstract: The principal aim of the invention is a cleat (100) for a blade foot (58) of a blade (48) of a propeller (32) of a turboengine (1), characterised in that it is open-work to allow the discharge of ventilation airflow of the blade foot (58).

Abstract: The main aim of the invention is a propeller (32) for a turboengine (1) comprising a plurality of blades (48) and a blade support ring (47) provided with housings (50), each receiving a pivot (52) bearing the foot (58) of one of said blades (48), characterised in that at least one of the pivots (52) is equipped with at least one counterweight system (90, 91) provided with at least one inner channel (93, 96) for airflow ventilation discharge (F1, F3) for capturing and guiding said airflow directly in contact with the blade foot (58) borne by said at least one of the pivots (52).

Abstract: An arrangement with a nacelle and a radiator of a wind turbine is provided. The nacelle is rotatable connected with the radiator. Thus, a joint component of the wind turbine is built by these elements. The connection is constructed and arranged such that the radiator is allowed to pivot between a first position and a second position. The radiator is locked in the first position and projects above the nacelle when the radiator is used to remove heat from the nacelle to the environment. When the radiator is locked in the second position the radiator is close to a side of the nacelle. Thus a minimum height of the joint component is achieved.

Abstract: A cooled turbine blade having a base and an airfoil, the base including cooling air inlet and an internal cooling air passageway, and the airfoil including an internal heat exchange path beginning at the base and ending at a cooling air outlet at the trailing edge of the airfoil. The airfoil also includes a “skin” that encompasses a tip wall, an inner spar, a plurality of inner spar cooling fins extending from the inner spar to the skin, and a plurality of trailing edge cooling fins extending from the pressure side of the skin to the lift side of the skin aft of the inner spar.

Abstract: A gas turbine engine airfoil has a hollow airfoil section extending chordwise between a leading edge and a trailing edge. The airfoil has a leading edge cooling passage and a separate serpentine passage for cooling a remaining portion of the airfoil. The serpentine passage has at least three segment serially interconnected in fluid flow communication. The leading edge cooling passage and the serpentine cooling passage have separate coolant inlets. The coolant inlet of the serpentine passage comprises a primary inlet branch connected in fluid flow communication with a first one of the segments of the serpentine passage and a secondary inlet branch connected in flow communication with a last one of the segments, thereby providing for a portion of the flow passing through the coolant inlet of the serpentine passage to be directly fed into the last segment of the serpentine passage.

Abstract: A blade for a rotor of a wind turbine, said blade comprising a blade body element provided with a carrier surface to accommodate a heating element, an electrically conductive, elongated and substantially planar heating element disposed upon the carrier surface to extend longitudinally substantially along at least the leading edge of the blade preferably at least about 50% of the length of the blade, more preferably at least about 60% and most preferably at least about 70% respectively, an electrical power supplying conductor element located at one end of the heating element, the conductor element substantially extending over the width of the heating element on both sides thereof and electrically coupling thereto, and a joint structure comprising at least one electrically conductive joint element and substantially covering, on both sides of the heating element, the portions of the electrical conductor element that extend over the width of the heating element, wherein said blade preferably contains an instance

Abstract: With a simple and low-cost structure, it is possible to introduce a sufficient amount of external wind while suppressing power consumption, and thereby, inside a nacelle and a tower are satisfactorily cooled. A wind turbine generator, in which a rotor head generates power by driving a generator installed inside a nacelle and in which the nacelle is installed at a top end of a tower, wherein an introducing vent that takes the external wind into an internal space in the wind turbine generator is provided at a portion of an outer circumference surface of the tower or the nacelle that receives positive pressure due to the external wind; and an exhaust vent that externally exhausts cooling air in the internal space is provided at a portion of an outer circumference surface of the tower or the nacelle that receives the negative pressure due to the external wind.

Abstract: An aerofoil typically for a blade or vane for a gas turbine engine comprises a pressure wall, a suction wall and a web that extends therebetween. One of the walls comprises an inner leaf and an outer leaf which defines a cavity, the other wall defines a first outlet, the aerofoil defines at least one first passage extending from the cavity through the web and to the outlet. Coolant in the cavity on one side wall of the aerofoil is thereby routed across the web to be used to cool the other wall by convention and formation of a coolant film.

Abstract: A turbine bucket includes an airfoil, a platform adjacent to the airfoil, and a shank adjacent to the platform. The shank defines a shank cavity, and a divider in the shank cavity creates a pressure differential across the shank cavity. A method for cooling a turbine bucket includes directing a fluid to a forward shank cavity and creating a pressure differential between the forward shank cavity and an aft shank cavity.

Abstract: A distributed heating system for a power train of a ram air turbine, which ram air turbine has a stowed position and a deployed position, has at least one electrical resistance heater element, with each electrical resistance heater element located proximate at least one respective lubrication surface for the power train; and an electrical controller for coupling electrical power to each electrical resistance heater element when the ram air turbine is in the stowed position and ambient temperature falls below a desired level.

Abstract: A turbine vane or blade segment includes at least one airfoil extending radially outwardly from a radially inner band. A plurality of cooling passages are formed in the radially inner band in fluid communication with an internal plenum in the airfoil and exiting the inner band via a plurality of exit holes in the one of the axially-extending side edges of the inner band. The plurality of exit holes are confined to a region along the one of the axially-extending side edges where static pressure PS along the one of the substantially axially-extending side edges lies in a pressure range substantially between the stage inlet total pressure PT and a pressure that is substantially about 1.5 times the dynamic pressure range ?PD, below the stage inlet total pressure.

Abstract: Voids, cracks or other similar defects in substrates of thermal barrier coated superalloy components, such as turbine blades or vanes, are filled with resin, without need to remove substrate material surrounding the void by grinding or other processes. The resin is cured at a temperature under 200° C., eliminating the need for post void-filling heat treatment. The void-filled substrate and resin are then coated with a thermal barrier coating.

Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a body portion, a cooling circuit disposed within the body portion and including at least a first cavity and a microcircuit in fluid communication with the first cavity. A plunged hole intersects at least a portion of the microcircuit.