Abstract: A gas turbine engine system includes a disk and an airfoil. The disk includes a first rail, a second rail, a retention slot located between the first and second rails, and a ridge extending radially outward from the second rail. The airfoil is engaged with the retention slot, and includes a platform with an upstream angled portion, a downstream angled portion, and a notch defined in the platform. The ridge of the disk extends at least partially into the notch of the platform.

Abstract: A segment for a knife edge seal includes an arcuate segment with a first end with a first end surface and a second end with a second end surface. The first end surface and the second end surface are complementary and overlapping when the first end surface and the second end surface interface with ends of adjacent segments.

Abstract: A method of fabricating a lobed structure for a gas turbine flow mixer having an annular upstream portion extended downstream by a portion forming a multilobed skirt, the method comprising: making a fiber preform (100) out of refractory fibers and having a shape corresponding to the shape of the lobed structure to be fabricated, from a plurality of component elements of fiber texture that are assembled together and shaped by means of tooling of a shape corresponding to the shape of the lobed structure to be fabricated so as to obtain an assembled fiber preform having a first preform portion (111) corresponding to the annular portion of the lobed structure and a second preform portion (112) corresponding to the multilobed skirt of the lobed structure, the component elements of the fiber preform being assembled together at least in part along connection lines (121) extending substantially in the flow direction of the flow past the lobes of the multilobed skirt preform portion; and densifying the assembled an

Abstract: Methods of assembling a rotor assembly of a gas turbine engine having a plurality of components. The method comprises, in one aspect, determining a static unbalance force of each component using the mass and the center of mass location, and determining an optimum assembly arrangement minimizing static unbalance forces. Optimal component stacking positions, among other things, may then be established.

Abstract: A gas turbine engine case having a working fluid flow, includes inner and outer case portions defining an annular duct for directing the working fluid flow, and a plurality of struts positioned within the annular duct and extending between the inner and outer case portions. The struts are welded to the inner and outer case portions with a first weld along a peripheral line of the respective struts and with second weld, of fillet type, in selected locations for additionally connecting a portion of each strut to the respective inner and outer case portions.

Abstract: A turbine blade assembly has a turbine blade with a root section and an airfoil section. The root section has one of a radially extending groove or flange, and a retainer element has the other of the groove and the flange. The groove receives the flange to hold the retainer element and the blade together. The retainer element has axial ends extending radially inwardly to secure a turbine blade assembly within a disk slot in a turbine rotor disk. A method is also disclosed.

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: A turbine rotor blade formed from three pieces with a pressure wall side piece and a suction wall side piece bonded to an intermediate piece so that a pressure side cooling circuit can be formed as a separate cooling circuit from a suction side cooling circuit. The intermediate piece has film cooling holes and blade tip cooling holes and trailing edge exit slots formed in it that are enclosed when the outer two pieces are boded to it.

Abstract: Method of assembling a rotor assembly of a gas turbine engine having a plurality of components. The method comprises in one aspect calculating the bending forces due to the mass distribution along the rotor. In another aspect, an optimization routine iterates different rotor arrangements, comparing the calculated bending moments to determine a set of component positions that minimizes the bending forces. In another aspect, mass corrections are optimized to balance the rotor assembly.

Abstract: Systems are provided for a blade installation tool. The blade installation tool may include a vertical guide having a vertical ram path. A ram may be disposed along the vertical guide. The ram can move along the vertical ram path between a lower position and an upper position at a height above the lower position. Gravity may drive the ram from the upper position toward the lower position to provide an impact force of the ram against a blade segment of a turbine or a compressor. The height of the upper position is variable so as to control the impact force.

Abstract: A system includes a rotor assembly with a first rotor component having a first set of bushing receptacles and a first set of bolt holes arranged about a first rotational axis of the first rotor component. The rotor assembly also includes a second rotor component having a second set of bushing receptacles and a second set of bolt holes arranged about a second rotational axis of the second rotor component. The rotor assembly includes a first set of bushings disposed in the first and second sets of bushing receptacles in a first installed configuration, wherein the first installed configuration of the first set of bushings is configured to align the first and second rotational axes with one another, and the first installed configuration of the first set of bushings is configured to bear at least a first portion of a torque during rotation of the rotor assembly.

Abstract: A turbine bucket includes an airfoil portion; a platform at radially inner end of the airfoil portion; a shank portion extending radially-inwardly of the platform; and a mounting portion extending radially-inwardly of the shank portion. The shank portion and the mounting portion have at least one axially-extending seal-engaging surface formed as part of a separable, non-integral isolation element that isolates the bucket from forces caused by a near-flow-path seal engaging the at least one axially-extending seal-engaging surface.

Abstract: A variable stator vane assembly for a gas turbine engine includes a variable stator vane and a non-structural fairing on the variable stator vane.

Abstract: Disclosed is a nacelle for a wind turbine which includes a generator, a load-carrying structure, a support structure, an electrical system, a yaw system, a control system and a housing. The generator includes a rotating part and a stationary part and the stationary part is connectable to the load-carrying structure. The load-carrying structure includes the yaw system and the control system. The support structure includes the electrical system and the support structure is connectable to the load-carrying structure. The housing is segmented and is connectable to at least the load-carrying structure. The generator, the load-carrying structure and the support structure are separate modules and the separate modules and the segmented housing are connectable at an erection site of the wind turbine to build the nacelle.

Abstract: A turbomachine blade made of composite material including a fiber reinforcement obtained by three-dimensional weaving of yarns and densified by a matrix, comprises a first portion constituting an airfoil and a blade root. The first portion constitutes a single part with at least one second portion constituting a blade inner platform, said blade then lacking a blade anti-tilting wall, or a blade anti-tilting wall, said blade then lacking a blade inner platform. The first portion also constitutes a single part with at least one third portion constituting a blade outer platform spoiler plate, said blade then lacking a blade outer platform wiper plate, or a blade outer platform wiper plate, said blade then lacking a blade outer platform spoiler plate.

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: The application describes an apparatus for and a method of mounting wind turbine blades on a wind turbine tower. A number of guide rods 94 are provided in the vicinity of the blade root and hub for connection to corresponding socket sections 96. The guide rods 94 and socket sections 96 are provided on respective ones of a wind turbine blade and a wind turbine hub to facilitate connection of one to the other. The guide rods 94 and the sockets 96 may be provide on the same or on different ones of the blade or hub. The guide rods and sockets allow the blade to be positioned at the hub in the correct rotational orientation to facilitate connection of the necessary fasteners.

Abstract: An inlet guide vane actuation apparatus is provided. The inlet guide vane actuation apparatus comprises an actuation ring with a first connector for connecting an actuator rod, wherein the first connector positions the actuator rod over the rotational axial center of the actuation ring, a plurality of crank rods with a first end connected respectively to a plurality of second connectors located on the rotational axial center of the actuation ring; and a plurality of cranks with each having a third connector connected respectively to a second end of the plurality of crank rods and respectively to vanes associated with a nozzle, wherein the third connector located on the rotational axial center of the actuation ring.

Abstract: A sealing assembly for use with a rotary machine is described herein. The sealing assembly includes a stator shroud coupled to the casing. The stator shroud includes an inner surface that at least partially defines the cavity within the casing. At least one stator labyrinth tooth extends outwardly from the stator shroud inner surface towards a rotor assembly positioned within the casing. At least one protective member is coupled to the stator shroud upstream from the at least one stator labyrinth tooth to facilitate reducing a flow of combustion gas across the at least one stator labyrinth tooth.

Abstract: A vertical axis turbine and method of making same is disclosed. The device and method comprise a plurality of blades rotatably disposed around an axis of rotation at a plurality of blade locations, each blade being twisted at a first angle about its longitudinal axis, each blade having its distal ends located a predetermined distance from the axis of rotation, each blade being bent at one or more central locations along the longitudinal axis so the one or more central locations are the same predetermined distance from the axis of rotation as the distal ends, each blade having a foil cross section perpendicular to the axis of rotation for maintaining unidirectional rotation of that blade about the axis of rotation in a fluid flow, and each blade having its longitudinal axis tilted at a second angle with respect to the axis of rotation.

Abstract: A multi-stage axial compressor incorporating a counter-rotational movement is provided with a series of rotors mounted along and driven by a driveshaft, and a geared counter-rotating outer casing. A planetary gear system is assembled along a static casing, which can be assembled as a forward or aft casing for the compressor. The bearings of the planetary gear system typically will be aligned concentrically with a center rotor drum assembly mounted along the single driveshaft. The counter-rotating drum assembly will be assembled over the rotor drum assembly and will be engaged by the forward and aft casings so as to provide for counter-rotation of selected ones of the rotors driven by the driveshaft of the compressor.

Abstract: The present invention relates to a transformer (100) for the transfer of electrical power from a nacelle (250) of a horizontal-axis wind turbine to a turbine tower (350) of said wind turbine whereby the nacelle (250) is in revolute attachment to the tower (350), comprising: a primary winding (200) adapted for attachment to the nacelle (250), and a secondary winding (300) adapted for attachment to the turbine tower (350), which windings (200, 300) are in revolute alignment with each other, and configured for transfer of electrical power by induction from the primary winding (200) to the secondary winding (300). It also relates to a method for assembly or disassembly of a wind turbine.

Abstract: A rotor (1) of a gas turbine compressor comprises a multiplicity of welded-together rotor disks (3a, 3b, 4, 5), of which two or more rotor disks (3a, 3b), in a radially outer region (9?), are welded together, and, in a radially inner central region (9), are abutment-joined together. Via the abutment-joining of two rotor disks (3a, 3b), a heat flow (8) radially outward from the center of the rotor (1) is achieved so that the material temperature of the rotor (1) can be kept below a predetermined level during operation. As a result, the service life of the rotor (1) can be increased. In one embodiment, one rotor disk (3a), on its surface, additionally has a recess (7) which can be cooled from outside. The rotor disks (3a, 3b) according to the invention, which are welded and abutment-joined together, can especially be used at the last point in the flow direction of the compressor.

Abstract: A system and method for securing a blade within a disk so as to eliminate the need for permanently deforming materials associated with the blade disk is disclosed. A recess is formed generally within each slot used to secure a blade within the disk. A retaining insert is positioned within the recess and a wedge insert is positioned within a slot of the retaining insert, such that a pressure is applied to the retaining insert thereby deflecting the retaining insert into a pre-set radial position to prevent axial movement of the blade within the slot of the disk.

Abstract: A vane assembly for a gas turbine engine according to an exemplary embodiment of this disclosure includes, among other possible features, a first platform, a second platform spaced from the first platform, and a first variable airfoil that extends radially across an annulus between the first platform and the second platform. One of a radial outer portion and a radial inner portion of the variable airfoil includes a rotational shaft and the other of the radial outer portion and the radial inner portion includes a ball and socket joint that rotationally connect the first variable airfoil relative to the first platform and the second platform.

Abstract: Contaminant build-up and cooling airflow looses are reduced in a turbine airfoil by joining root and airfoil cooling air passages thereof with a transition passage.

Abstract: A turbine blade growth pocket provides a feature to measure blade growth due to engine operation while maintaining dynamic characteristics of the turbine blade within acceptable limits by providing a variable radius fillet between the pocket and a side rail of the pocket.

Abstract: A method for the production of a fibrous metal structure by weaving with metal weft yarns and metal warp yarns. The method includes weaving the fibrous structure by successive weaving of metal clasps that are used as weft yarns. For the purpose of weaving, each of the arms of each of the metal clasps is introduced into at least one shed, each shed being formed by two warp yarns.

Abstract: The present application provides a method of installing an impingement cooling assembly in an inner platform of an airfoil of a turbine nozzle. The method may include the steps of positioning an insert within a cavity of the airfoil, positioning a core exit cover about an opening of the cavity, positioning an impingement plenum within a platform cavity, inserting an unfixed spoolie through an assembly port of the impingement plenum and into an airflow cavity of the insert, and closing the assembly port.

Abstract: A sectioned rotor is disclosed that includes a high temperature section. The high temperature section includes a first high temperature material section, a second high temperature material section; and a sectioned high temperature material section formed of a plurality of high temperature material subsection components. The sectioned high temperature material section is joined to the first high temperature material section and the second high temperature section. The plurality of the high temperature subsection components are independently formed of a nickel-based superalloy. A steam turbine having a sectioned rotor and a method for manufacturing a sectioned rotor are also disclosed.

Abstract: A turbomachine system includes a turbomachine that includes a rotor that includes a rotational axis, a first rotating segment having a first mating axial mount coupled to a first axial mount of the rotor in a first installed position and a first pin configured to insert into a first inserted position in both a first slot in the rotor and a first mating slot in the first rotating segment. The first pin in the first inserted position is configured to block axial movement of the first mating axial mount relative to the first axial mount. The turbomachine also includes a second rotating segment having a second mating axial mount coupled to a second axial mount of the rotor in a second installed position. The second rotating segment in the second installed position is configured to block removal of the first pin.

Abstract: A composite blade assembly for mounting on a turbine wheel includes a ceramic airfoil and an airfoil platform. The ceramic airfoil is formed with an airfoil portion, a blade shank portion and a blade dovetail tang. The metal platform includes a platform shank and a radially inner platform dovetail. The ceramic airfoil is captured within the metal platform, such that in use, the ceramic airfoil is held within the turbine wheel independent of the metal platform.

Abstract: A device for aligning tip shrouds includes a platform configured to connect to a blade, a first projection that extends circumferentially across at least a portion of the platform, and a first complementary alignment feature on the first projection. A method for aligning tip shrouds includes rotating a plurality of tip shrouds, wherein each tip shroud is coupled to a blade, and aligning adjacent tip shrouds by nesting a first alignment feature of a first tip shroud into a second alignment feature of a second tip shroud.

Abstract: A method for repairing turbine blades by replacing at least a part of the blade profile, the method having: a) manufacture of a replacement blade part; b) separation of the damaged area with a standardized cutting plane, leaving behind a remaining blade; c) matching of the replacement blade part to the actual geometry of the remaining blade; d) connecting or joining of the replacement blade part to the remaining blade by soldering of at least one web and welding of an outer contour.

Abstract: Systems, methods and devices adapted to ease installation of turbine bucket assemblies about a rotor and to reduce related stress concentrations in the rotor are disclosed. In one embodiment, an insert includes: a base portion adapted to complement an entry slot in a rotor of a turbine; and a neck portion extending radially outboard from the base portion, the neck portion adapted to complement a post of the rotor to form a substantially continuous dovetail about the rotor.

Abstract: A method for manufacturing a hollow structural turbomachine vane, the method including forming a first cavity in a first face of a first block; assembling by diffusion bonding the first block and a second block, the first face of the first block being positioned facing a second face of the second block, the first cavity thus forming a closed cavity; machining the block resulting from the assembly of the first block and the second block so as to obtain a vane including the closed cavity.

Abstract: An airfoil and method of fabricating an airfoil including a first and a second side coupled together at a leading and a trailing edge and extending there between. The airfoil includes a plurality of first chord sections having a first chord length and extending outward from one of the first side or second side of the airfoil at the leading edge and a plurality of second chord sections having a second chord length and extending outward from the one of the first side or the second side of the airfoil at the leading edge. The leading edge including spaced-apart wave-shaped projections defining a waveform. The configuration defining a three-dimensional crenulated airfoil configured to facilitate desensitization of an airfoil unsteady pressure response to at least one impinging upstream generated wake or vortex by decorrelating spatially and temporally and reducing in amplitude an unsteady pressure caused by interaction of the airfoil with the upstream generated wake or vortex.

Abstract: A rotor retaining system for a rotor assembly of a gas turbine engine includes a washer interlocking multiple retaining nuts to prevent relative rotation. The retaining nuts retain a rotor disc and a cover plate in position, respectively. A wire is provided to retain the washer in position and which may dampen vibration during engine operation.

Abstract: An exemplary turbomachine rotor assembly includes a pair of spaced rails that extend around a cylindrical surface to define a rotor hub. The rails define a space for receiving blades. Load slots are formed in one of the rails. A relief feature is formed in an opposite surface of an opposing rail. The load slots and relief feature utilized to move at least one of the blades into the space.

Abstract: A lock for constraining blades in a hub includes a flexible ring for constraining the blades from moving axially in the hub, a finger attached to the hub for preventing the ring from rotating relative to the hub and whereby the ring flexes about at least a partial circumference thereof if urged axially by the blades.

Abstract: A method for assembling a vane ring with a vane support of a vane assembly in a gas turbine engine is described, and includes flexing each of the radial loading elements into the resiliently flexed state simultaneously by sliding the radial loading elements against corresponding lead-in tapers. This can be achieved, for example, using a guide tool which includes a plurality of segments bearing the lead-in tapers and which is previously assembled to the vane support.

Abstract: In one aspect, a rotor hub assembly for a wind turbine is disclosed. The rotor hub assembly may generally comprise an inner hub including a plurality of hub segments assembled together and a hub enclosure including a plurality of enclosure segments assembled together. The hub enclosure may be configured to at least partially enclose the inner hub. In addition, the rotor hub assembly may include a plurality of support members extending between the inner hub and the hub enclosure.

Abstract: A turbomachine component is provided and includes a turbine blade, which is rotatable about a rotor of a turbine for power generation operations and a platform with which the turbine blade is to be assembled. The turbine blade is formed to define a main circuit having an appendage. The platform is formed to define a platform circuit, and a substantially radially extendible pathway configured to be coupled to the appendage and to the platform circuit.

Abstract: A turbocharger assembly includes a compressor wheel with a base surface, a nose surface, a z-plane disposed between the base surface and the nose surface and a bore extending from the base surface to the nose surface and a shaft that includes a first pilot surface disposed in the bore of the compressor wheel at a position between the z-plane and the nose surface, a second pilot surface disposed in the bore of the compressor wheel at a position between the z-plane and the base surface, and a recessed surface disposed between the first pilot surface and the second pilot surface. A nut adjustably disposed on the shaft adjacent to the nose surface can tension the shaft to apply a compressive load between the base surface and the nose surface of the compressor wheel. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.

Abstract: The present invention provides a hybrid turbomachinery component for use in a gas turbine engine. The hybrid turbomachinery component may be operative to direct the working fluid of the gas turbine engine and/or addi energy to the working fluid and/or extract energy from the working fluid. One or more portions of the hybrid turbomachinery component are made from one material, and other portions of the hybrid turbomachinery component are made from another material.

Abstract: A blade of a wind turbine and a method to manufacture the blade are provided. The blade of the wind turbine includes at least one vortex-generator. The vortex generator is constructed and arranged at the blade in a way that it contributes to the aerodynamic characteristics of the blade. The blade includes a recess, which is constructed and arranged to receive at least a part of the vortex-generator. The vortex generator is fixed in the recess. The recess is at least partly arranged and at least partly embedded in a layer of paint of the blade-surface. The recess is established by a former plate, which is arranged on the surface of the blade before the blade-surface is painted and while the recess is established by removing the former plate after the painting is finished.

Abstract: The present application provides a cover plate assembly for use with a rotor disk. The cover plate assembly may include a radial flange extending from the rotor disk, a flange aperture extending through the radial flange, a cover plate segment with a fastening aperture and a hook for receiving the radial flange, and a fastener extending through the flange aperture and the fastening aperture.

Abstract: A rotor blade assembly tool for coupling a plurality of circumferentially spaced rotor blades to a rotor disc of a turbine rotor assembly, includes a base ring with an array of circumferentially spaced resilient fingers axially extending from the base ring.

Abstract: A fastening assembly for blades of turbomachines through which axial flow can take place, preferably compressors, includes a blade carrier having a lateral face, in which retaining groves are distributed along the circumference, with blades being inserted in the grooves, wherein a resilient tensioning element is provided between each groove base and the underside of the respective blade foot, the underside being located opposite of the groove base. The tensioning element is supported on the respective underside and on the respective groove base in a pretensioning manner, wherein a channel is provided both in the groove base and in the underside, with the tensioning element resting in the channels.

Abstract: Non-uniform variable stator vanes for a single stage of a gas turbine engine stage include non-uniform airfoils with a non-uniformity between airfoils of first and second portions of the stator vanes. The variable stator vanes may further include all outer buttons, from which the airfoils inwardly extend, in all of the variable stator vanes being equally sized and shaped and the same all inner buttons if used. The airfoils in the first and second portions may be counter-clockwise and clockwise biased respectively with respect to a nominal airfoil position. The airfoils in the first and second portions may be counter-clockwise and clockwise leaned respectively with respect to the nominal airfoil position. Outer ends of the airfoils in the first and second portions may be counter-clockwise and clockwise shifted respectively with respect to the nominal airfoil position.