Abstract: A wind turbine rotor assembly comprises: a rotor support; a rotor which is rotatably mounted to the rotor support; and a base support; wherein the rotor support and base support are provided with engagement means which allow said rotor support and base support to engage with each other so that when the rotor support and base support are moved together a hinged connection is formed between the rotor support and base support, which hinged connection allows the rotor support to rotate relative to the base support during installation or decommissioning of the rotor.

Abstract: A rotor assembly for a gas turbine engine, with an annular sleeve having an inner member connected around the shaft to rotate together therewith and having an outer member with a first end connected to the inner member, the outer member defining an annular continuous frustoconical inner surface angled such as to extend closer to the central axis near the first end. A rotor disc includes an annular protuberance extending radially inwardly of the outer member and forced toward the first end, and having an annular continuous frustoconical outer surface complementary to the inner surface of the outer member and in torque-transmitting engagement therewith. The assembly includes means for axially pressing the sleeve and the disc against one another to maintain the complementary frustoconical surfaces in torque-transmitting engagement. A method of engaging a rotor disc to a driving shaft in a gas turbine engine is also provided.

Abstract: A method of fabricating a single-piece part for a turbine engine by diffusion bonding, the method including making a blank for the part around a mandrel, the blank including a plurality of coaxial and superposed annular layers of independent rings of metal wire that are stacked on one another around the mandrel, and subjecting the blank to hot isostatic pressing to obtain a single-piece part, and optionally machining the part.

Abstract: An assembly device for assembling and disassembling a rotor of a turbomachine with rotor disks that are clamped together by at least one tie rod is provided. The assembly device includes a turning block that is secured to a base and a securing device that secures the rotor against tilting. The rotor is arranged in a transversal manner in relation to a horizontal plane of the base and pivotably mounted on the turning block. The securing device is fixed to the base by several supports and the turning block is arranged inside the surface of the base that is clamped by the supports. Large forces and torque coming from the rotor that is arranged in a perpendicular manner are guided from the securing device to the base.

Abstract: The present invention relates to a method for replacing an inner disk element of a blade integrated disk wherein the blade integrated disk has a plurality of recesses in the form of axial through-bores in the joining area. The method begins with filling the axial through-bores, after which the inner disk element of the blade integrated disk is separated from the remaining blade ring. Next a new inner disk element is inserted into the remaining blade ring and the new inner disk element and the remaining blade ring are joined. Finally the axial through-bores are restored.

Abstract: A turbine engine rotor assembly includes a turbine engine rotor disk that extends axially along a centerline between a first disk end and a second disk end, and radially to an outer disk surface. The rotor disk includes one or more blade retention slots arranged circumferentially around the centerline. A first of the blade retention slots extends axially into the rotor disk from a disk end surface at the first disk end to a slot end surface, and radially into the rotor disk from the outer disk surface to a slot base surface.

Abstract: A method for assembling a modular foundation of a wind turbine having a base and a plurality of foundation sections includes positioning the base of the foundation on a support surface, arranging a plurality of tensioning elements so as to extend from the base to a second location spaced from the base, and stacking a plurality of foundation sections on the base by guiding the foundation sections from the second location toward the base using the tensioning elements. A modular wind turbine foundation includes a base positioned on the seabed; a plurality of tensioning elements extending from the base to a location adjacent the surface of the water; and a plurality of serially stacked foundation segments on top of the base.

Abstract: A fixture for connecting rotors of a rotary machine includes: an axial member provided with a column-like fitting portion which is disposed inside of a first bolt hole and fits the first bolt hole; and a sleeve provided with a cylindrical fitting portion which is disposed inside of a second bolt hole and fits the second bolt hole. The axial member further includes a tapered portion which is formed on an end portion of the column-like fitting portion, and is gradually reduced in diameter from the first bolt hole toward the second bolt hole. The cylindrical fitting portion of the sleeve is formed with a tapered hole which is gradually expanded in diameter from the second bolt hole toward the first bolt hole around an axis of the sleeve.

Abstract: An exemplary turbine engine assembly includes a first shaft that is rotatably driven by a second shaft of a gas turbine engine and a compressor hub driven by the first shaft. The compressor hub is within a compressor section of the gas turbine engine. An epicyclic gear train is driven by the first shaft. A common attachment point secures the first shaft and the compressor hub to the second shaft.

Abstract: A cooling fan shroud comprises multiple, functionally identical sections that form a ring-like structure that completely surrounds the fan when the shroud is installed onto an aperture plate or other structure. The shroud makes the cooling system more efficient by improving air flow at a given fan speed by reducing fan tip clearance, and increasing air flow due through the fan. An alternative, single piece shroud is also provided which can be retrofitted to an existing cooling system.

Abstract: In a stator, segment coils each consisting of a pair of straight portions connected with a connecting portion in a U-like shape are set in slots of a stator core. Each straight portion has distal end parts protruding on an opposite side to the connecting portions. The distal end parts in odd-numbered positions from an outer or inner circumferential side in a radial direction are twisted in one direction and shaped radially outward and the distal end parts located in even-numbered positions are twisted in an opposite direction to the one direction and shaped radially inward to be joined to each other on the same circumference by welding.

Abstract: A method for providing a shallow-angled hole through a thermal barrier coated component in accordance with one aspect thereof, includes a step of applying a pulse laser beam to pre-drill the hole through a base metal of the component. A thermal barrier coating is then applied to the base metal, covering the pre-drilled hole in the base metal. A further step is conducted to apply the pulse laser beam through the thermal barrier coating a location to coincide with pre-drilled hole in the base metal in order to complete the formation of the hole extending through the component.

Abstract: A method of fabricating an integrally bladed rotor of a gas turbine engine according to one aspect, includes a 3-dimensional scanning process to generate a 3-dimensional profile of individual blades before being welded to the disc of the rotor. A blade distribution pattern on the disc is then determined in a computing process using data of the 3-dimensional profile of the individual blades such that the fabricated integrally bladed rotor is balanced.

Abstract: A balancing weight clip with a mass adapted to balance a rotor assembly of a gas turbine engine, includes a weight portion, a first flange engaging portion and a second flange engaging portion extending from the weight portion, each being engageable with a sidewall of at least one recess located on an edge of a flange of a disc of the rotor assembly. Each flange engaging portion is provided with a hook engageable with a mating groove provided on a face of the flange. At least one of the first and second flange engaging portions is resiliently biased so that the first and second flange engaging portions are elastically moveable away from one another to removably secure the balancing weight clip to the flange and engage each hook with the mating groove.

Abstract: A method for attaching a rotor of a wind turbine generator and a method for constructing a wind turbine generator are provided, with which the rotor blades can be prevented from breaking and with which the construction costs can be reduced. The present invention includes: an assembly step (S1) in which a plurality of wind-turbine rotor blades are attached to a rotor head to assemble the rotor on the ground; a wire attaching step (S2) in which a first wire is attached to a first hoisting portion provided on a rotation axis of the rotor and in which a second wire is attached to a second hoisting portion provided at a position away from the rotation axis; a hoisting step (S3) in which the rotor is hoisted with the first wire; a rotor raising step (S4) in which the first wire is extended so that the rotor is hoisted with the second wire; and a rotor attaching step (S6) in which the rotor hoisted with the second wire is attached to the nacelle.

Abstract: A fixation device for fixing a shaft connecting a rotor and a generator of a wind turbine, the fixation device comprising: a rotor lock for locking the shaft providing a locking clearance; and a rotor brake for braking the shaft; wherein the rotor lock is arranged for positioning the shaft in a selectable angular position within the locking clearance of the rotor lock.

Abstract: The invention relates to a method for manufacturing a steam turbine low-pressure or medium-pressure module deflector, said deflector comprising an internal ring and an external ring as well as vanes, said method comprising a step of welding said vanes to said rings. The main characteristic of a method according to the invention is that the welding step is preceded by a step of automatically machining the ends of each vane to create a peripheral recess around each of said ends.

Abstract: A stator of an electric motor or generator comprises a core formed of ferromagnetic material having a plurality of teeth arranged circumferentially about an axis. In one aspect of the invention, at least one retaining member connects the end portions of at least two of the teeth to each other in a manner inhibiting relative movement between said tooth end portions. By inhibiting relative movement between said tooth end portions, vibration is reduced. Vibration can also be reduced by welding interior surfaces of a core to each other. Reducing the vibration reduces the noise emissions of the stator during operation.

Abstract: A method for drilling a shallow-angled hole through a thermal barrier coated component, in accordance with one aspect thereof, includes a step of applying a pulse laser beam with a first setting to drill a section of the hole substantially within a thermal barrier coating of the component. A further step is conducted to apply the pulse laser beam with a second setting through the initiated hole to further drill through a remainder of the component to complete the formation of the hole extending through the component.

Abstract: A method of assembling a blade array includes the step of inserting a blade having a platform into a rotor. The blade includes a pocket radially beneath the platform that includes an interference feature. The blade corresponds to one of first and second blades that are scaled versions of one another. The method includes the step of selecting a damper seal, and inserting the damper seal into the pocket. The damper seal corresponds to one of first and second damper seals. The first damper seal cooperates with the interference feature thereby permitting the first damper seal to fully seat within the pocket. The second damper seal is obstructed by the interference feature thereby preventing the second damper seal from fully seating within the pocket.

Abstract: A deployable aerodynamic component configured to be mounted to a wind turbine. The wind turbine includes at least one rotor blade. The deployable aerodynamic component configured to be positioned in front of an inner portion of the at least one rotor blade, and is structurally configured to cover a substantial portion of the inner portion of the at least one rotor blade in a wind direction during deployment of the deployable aerodynamic component and to allow the passage therethrough of an incoming wind when non-deployed. Further described is a wind turbine including the above-described deployable aerodynamic component and method for aerodynamic performance enhancement of an existing wind turbine, wherein the method includes mounting the above-described deployable aerodynamic component to a wind turbine.

Abstract: Devices and systems for transporting a material suspended in a fluid, e.g., pulverized coal, that can be assembled about a rotary element are disclosed. The devices and systems comprise a first portion or half of a fan wheel assembly, a second portion or half of a fan wheel assembly, and a plurality of splice plates for connecting the first portion of the fan wheel assembly to the second portion of the fan wheel assembly about the rotary element. Methods of manufacturing and assembling the sectionalized devices and systems are also provided.

Abstract: A tapered roller bearing element includes a first end and a second end, the second end having a second end radius. There is an apex ring between the two ends having an apex ring radius. There is also a base cone extending between the first end and the apex ring, the base cone tapering outwardly at a base cone angle. In addition, a relief cone extends between the apex ring and the second end, the relief cone tapers inwardly at a relief cone angle, and relief cone angle is larger than the base cone angle.

Abstract: A water paddle comprising a first shaft having a blade end and a free end and a second shall having a blade end and a free end, a first cog collar located on an exterior surface of first shaft and having a first set of teeth extending radially from a mating end of first cog collar and accessible to the user's fingers, a second cog collar located on an exterior surface of second shaft and having a second set of teeth extending radially from a mating end of second cog collar and accessible to the user's fingers, second set of teeth mateable with first set of teeth to prevent rotational movement between shafts, a ferrule extending from the free end of second shaft, a clip lip member located on an interior surface of the ferrule, and a spring tab mechanism located within an interior surface of first shaft and includes a body having corresponding resilient arms each having a displaceable tab supported thereon engageable with a set of push button holes located on first shaft.

Abstract: A method for mounting a wind turbine blade to a wind turbine hub by use of a crane boom is provided. The orientation of the blade is kept substantially horizontal when the blade is lifted off the ground and mounted to the rotor hub. Control wires which connect the blade via the crane boom to a winch arrangement are used for keeping the blade orientation substantially horizontal in addition to at least one bearing wire for bearing the blade weight.

Abstract: A rotor assembly for a gas turbine engine includes a rotor configured for rotation about an engine axis, the rotor including an aft surface including a rotor slot and a cover plate attached to the aft surface of the rotor, the cover plate including a tab received within the rotor slot and a cover plate slot aligned with the rotor slot. A lock assembly disposed within the rotor slot holds a position of the cover plate relative to the rotor. The lock assembly includes a key portion conforming to the rotor slot, a lock portion engageable with a surface of the rotor slot and a threaded member for holding the lock assembly within the rotor slot.

Abstract: A method of fabricating an airfoil includes the steps of fabricating a first core including a first plurality of ribs defining a first plurality of passages of a completed airfoil, and fabricating as second core including a second plurality of ribs defining a second plurality of passages of the completed airfoil. The second plurality of ribs includes a plurality of standoffs. The plurality of standoffs set a spacing between the first plurality of ribs and the second plurality of ribs to define a spacing between the first plurality of channels and the second plurality of channels of the completed airfoil. The airfoil is then molded about the core assembly. Once completed, the core assembly is removed to provide a completed airfoil incorporating multiple microcircuits with a desired stability and structural integrity.

Abstract: An apparatus and method for protecting an inner radial surface of a housing of a turbomachine from corrosion. The method includes tapering the inner radial surface of the housing and a corresponding outer radial surface of a corrosion-resistant liner, and heating the housing to increase a diameter of the inner radial surface of the housing. The method also includes inserting the corrosion-resistant liner at least partially into the housing, and attaching the corrosion-resistant liner to the inner radial surface of the housing a solid-state bonding process.

Abstract: An airfoil includes an airfoil working portion and an adjoining endwall. The endwall has a leading edge, a trailing edge, a first mateface, and a second mateface that collectively define a perimeter of the endwall, with the first and second matefaces arranged opposite one another. A forward zone is defined by the endwall that extends to the leading edge. The first and second matefaces are each oriented at an angle ?II relative to radial in the forward zone. An aft zone is defined by the endwall that extends to the trailing edge. The first and second matefaces are each oriented at an angle ?II relative to radial in the aft zone. The angles ?II and ?II are not equal. A middle zone is defined in between the forward and aft zones, and the first and second matefaces transition between the angles ?II and ?I in the middle zone.

Abstract: A method for installing an inner blade part or a wind turbine blade and to a lifting bracket for use in performing said method, e.g., a inner blade part for a partial pitch wind turbine blade comprising an inner blade part and an outer blade part, said inner blade part comprising a first flange for connection to a hub flange at a wind turbine hub and a second flange for connection to an outer blade part, said flanges all comprising a number of bolts and/or bolt holes. The lifting bracket has a flange for connection to a suitable number of bolts and/or bolt holes at said second flange on the inner blade part, the flange having a first surface and an opposite second surface arranged for interfacing with the first flange, and further the lifting bracket also has at least one lifting lug and at least one counter weight.

Abstract: The present invention relates to a method of joining a hub 11 and a shroud 12 of an impeller 10, either one of which has blades 13 integrally formed thereon, by welding. During the welding, in an upright state in which the hub 11 is placed to face a mount surface, the hub 11 and the shroud 12 are placed on top of each other to form an assembled body 10. Welding is performed on the assembled body 10 covered with a heat insulating jacket 30(a to g), the jacket 30 covering the assembled body 10 except an open region (OP) and an inflow port 14IN required for welding. When welding of one open region OP is completed, a new open region OP is formed by moving the heat insulating jacket 30 with respect to the assembled body, and then the next welding is performed.

Abstract: An axial flow turbine diaphragm is constructed without welding or other metal joining techniques as an annular array of static blade units. Each blade unit comprises an aerofoil and radially inner and outer platforms integral with the aerofoil. The radially inner platform consists of a segment of the inner diaphragm ring and the radially outer platform consists of a segment of the outer diaphragm ring. At least the outer ring segment has engagement features that mechanically engage with complementary engagement features on neighbouring outer ring segments in the annular array of blade units, the engagement features acting to mechanically interlock neighbouring outer ring segments and produce a self-supporting turbine diaphragm.

Abstract: The invention relates to a Magnus rotor comprising a cylindrical body of revolution for converting wind power into a feed force using the Magnus effect. The Magnus rotor comprises: a rotational shaft about which the body of revolution rotates; a support member on which the body of revolution is mounted; and a body of revolution which has means for the reinforcement thereof. The body of revolution is primed in at least two planes arranged at a mutual spacing in the axial direction perpendicular to the rotational shaft of the body of revolution in order to accommodate balancing weights. The invention further relates to a method for balancing a body of revolution according to the invention.

Abstract: A damper (2) for damping a blade movement of a turbomachine (1), and to a method for producing the damper (2). The damper (2) has at least one side surface (21, 21?) which can be brought into frictional contact with a friction surface of the turbomachine (1) in order to damp a blade movement. The side surfaces (21, 21?) are asymmetrically convex in shape.

Abstract: A process for forming a firtree slot in a disc of a bladed rotor assembly for a gas turbine engine may include making a first pass with a machining quill to form a rough profile of the firtree slot, making a second pass with an inclined machining quill having the shape of one of the finished side wall profile of the firtree slot and avoiding engagement with the other side, and making a third pass with an inclined second quill having the shape of the other of the finished side wall profile of the firtree slot and avoiding engagement with the other side, in order to provide a firtree slot for receiving and fixing the root of a blade.

Abstract: An airfoil includes a body that has a platform, an airfoil extending outwardly from a side of the platform and a root extending outwardly from another side of the platform. A member is connected in an articulated joint to the body.

Abstract: An airfoil includes an airfoil body that defines a longitudinal axis. The airfoil body includes a leading edge and a trailing edge and a first sidewall and a second sidewall that is spaced apart from the first sidewall. The first sidewall and the second sidewall join the leading edge and the trailing edge and at least partially define at least one longitudinally elongated cavity in the airfoil body. A plurality of loose particles is enclosed in the at least one longitudinally elongated cavity.

Abstract: A method for welding superalloy components at ambient temperature conditions while reducing the propensity of the superalloy material to crack as a result of the weld. A root pass region of the weld is formed using a filler material that exhibits ductility that is higher than that of the base superalloy material. The ductile material mitigates stress in the root region, thereby preventing the formation of cracks. A remaining portion of the weld is formed using a filler material that essentially matches the base superalloy material. The method may utilize a pre-weld heat treatment to grow a gamma prime precipitate phase in the superalloy material, a chill fixture to remove heat during welding, a relief cut to reduce stress in the root region, and a conventional post-weld heat treatment.

Abstract: An impeller is formed of two parts, i.e., an inner peripheral side part and an outer peripheral side part. The inner peripheral side part is molded in a cylindrical shape. The outer peripheral side part is formed by integrally molding an annular disc externally fitted to an outer peripheral surface of the inner peripheral side part, a plurality of blades provided at an interval in a circumferential direction on a surface that faces the other side in the axis line direction of the annular disc and forming al flow path extending in a radial direction, and a cover covering the plurality of blades from the other side in the axis line direction and having an insertion hole to which the inner peripheral side part is inserted in the axis line direction at an interval in a radial direction.

Abstract: Disclosed is a holding device for holding a hub to be installed at a nacelle. The holding device includes a carrier element with a first connection interface configured to connect the holding device to a lifting system, and a second connection interface configured to connect the device to a blade pitch bearing of the hub. Further disclosed is a pitch operating device for operating a blade pitch angle adjustment device of a hub to be mounted to a nacelle. The pitch operating device includes an actuating unit and a power interface for connecting the pitch operating device to the blade pitch angle adjustment device. Further disclosed is a hub installation system including such a holding device and such a pitch operating device. Further, a method for installing a hub at a nacelle and a method for dismounting a hub from a nacelle are described.

Abstract: A method is provided for extending the service life of a used metallic compressor wheel having a damaged surface. The method generally comprises the steps of inspecting the used compressor wheel for material discontinuities such as fatigue cracks and, if fatigue cracks exceeding a predetermined length are not present, renewing the used compressor wheel such as by peening. The inspection process comprises conducting a non-destructive examination of the used compressor wheel to detect cracks larger than those which would fall generally within the compressive stress zone that is generated by peening.

Abstract: A tool to enable removal of a wind turbine blade, wherein the weight of the blade itself secures the blade without need for additional fixation. The tool includes an articulated structure, composed of an upper part and a lower part articulated to each other; a cradle-shaped support attached to the lower part of the structure and configured to house a blade, the cradle-shaped support having two portions being moveable to each other; a hooking element which allows the tool to be suspended from a first crane; and springs fixed to the structure for exerting an aperture force on the structure, which allows automatic aperture of the structure in the absence of blades in the interior of the cradle.

Abstract: An exemplary fan includes a hub and an impeller. The hub is made of metal, and includes a flange. The impeller is made of plastic. The impeller is formed around the hub and has the flange embedded therein. A method for manufacturing the fan is also provided.

Abstract: In manufacturing a multi-finger pinned root pin-coupling a turbine blade made of a high-strength material and a rotor disc, a reamer used to ream a pin insertion hole formed through a turbine blade attachment base is removed from the pin insertion hole while being rotated so as to cause a scratch formed by a chip on the inner surface of the pin insertion hole to be inclined with respect to the axial direction of the pin insertion hole. This brings the direction of the scratch on the inner surface of the pin insertion hole and the direction of tensile stress generated on the inner surface of the pin insertion hole adequately close to be parallel to each other. As a result, the fatigue strength reduction caused by the scratch can be inhibited.

Abstract: An insulator for a stator assembly includes at least a first insulator adapted to be mounted to the stator core and structured to insulate the stator core from the coils. The at least one insulator includes structure to perform at least one additional function. For example, the structure may include a support member to support and/or locate the PCBA on the stator core, a wire guide to guide cross-over wires that form a connection between coils, and/or positioning structure to precisely position the PCBA with respect to the coils.

Abstract: A process is provided for producing a rotor which is made by welding together disk-shaped and/or drum-shaped elements, in particular disks, wherein a device is used to join the disks together axially in sequence along a longitudinal axis and the disks are welded in a two-stage welding process. As they are joined together, the disks are stacked axially in the vertical direction. A first welding process takes place in a vertical orientation of the stacked disks, followed by a second welding process in a horizontal orientation of the stacked disks.

Abstract: A clip to connect a blade to a rotor disk, the blade with a root and a tip in a spanwise direction, and a leading edge and a trailing edge in a chordwise direction, the root with a bottom surface, includes a locking mechanism shaped to engage a complementary slot extending into the bottom surface of the blade root in the spanwise direction; a support connected to the locking mechanism extending the length of the bottom surface of the root in the chordwise direction; and first and second arms extending radially inward converging in an axial direction so that the arms are closer at their distal ends to engage the rotor disk.

Abstract: A method of forming a leading edge protection component includes depositing particles using a cold spray process on a mandrel to form a leading edge protection component; and removing the leading edge protection structure from the mandrel. The leading edge protection can be formed in one or more pieces and involve using one or more mandrels.

Abstract: A balanced rotor comprising a circumferential slot and a plurality of aerofoils each secured in the slot by a respective root, the root having a root block having circumferentially facing flanks and a seal wing extending circumferentially from one of the flanks, characterised in that the seal wing has a notch engaging a balance weight positioned between adjacent roots.

Abstract: A platform for supporting a nozzle guide vane for a gas turbine is provided. The platform has a gas passage surface arranged to be in contact with a streaming operation gas, and a cooling channel for guiding a cooling fluid within the cooling channel formed in an inside of the platform. A cooling portion of an inner surface of the cooling channel is in thermal contact with the gas passage surface. The platform is an integrally formed part representing a segment in a circumferential direction of the gas turbine. The cooling channel has a first cooling channel portion and a second cooling channel portion arranged downstream of the first cooling channel portion with respect to a streaming direction of the operation gas. The first cooling channel portion and the second cooling channel portion are interconnected.