Abstract: The invention relates to a compressor blade of a compressor which, along a main axis, comprises a blade base, a platform area and an adjacent blade profile having a profile tip. The blade profile is configured by a convex wall at the suction end and a concave wall at the pressure end opposite the wall at the suction end. These surfaces extend, with respect to a flow medium, from a leading edge to a trailing edge, a profile center line extending in the center between the two. A front face is arranged on the profile tip at an angle to the main axis, a sealing lip at least partially extending from the leading edge to the trailing edge and the blade profile including the sealing lip having a blade profile height extending in the direction of the main axis. In order to allow for an inexpensive compressor blade having improved aerodynamic properties and a modified sealing lip while having the same sealing properties, the height of the sealing lip is less than 2 percent of the height of the blade profile.

Abstract: Secondary air flow is provided for a ducted fan having an engine core driving a fan blisk. The fan blisk incorporates a set of thrust fan blades extending from an outer hub and a set of integral secondary flow blades extending intermediate an inner hub and the outer hub. A nacelle provides a first flow duct for the thrust fan blades and a secondary flow duct carries flow from the integral secondary flow blades.

Abstract: A rotary drum of an axial compressor having a web made of composite material has an upstream flange for fastening the fan, a segment having a sealing flange upstream, a segment with a groove adapted to receive the bases of the vane of a first row of vanes, a segment with a groove adapted to receive the bases of the vane of a second row of vanes, and a segment with a groove adapted to receive the bases of the vane of a third row of vanes. These segments are made of metallic material mostly for reasons of mechanical resistance to the centrifugal forces. The segments are connected to each other with web segments made of composite material. The ends of the metallic segments have a dovetail-shaped section in a longitudinal plane that is able to ensure a positive connection with the composite material.

Abstract: A method for providing a disc of a bladed rotor for use in a gas turbine engine including the steps of determining the location of blade fixing slots to be formed on the disc to receive the roots of respective blades, determining a virtual profile of each slot on the disc, and forming, prior to the slots being formed in the disc, a narrow, axial pilot slot centrally of the virtual profile of each slot.

Abstract: A fan blade retaining and sealing ring assembly for an aft side of a bladed disk assembly is disclosed herein. The ring assembly includes an inner ring operable to prevent aft movement of a fan blade positioned in a slot formed in the blade disk. The ring assembly also includes an outer ring operable to seal against a platform of the fan blade. The inner ring and the outer ring are formed from different materials.

Abstract: A method for assembling a rotating machine includes providing a rotating element. The method also includes forming a first dovetail slot having a first axial length within a portion of a rotating element. The first dovetail slot is substantially parallel to an axial centerline of the rotating element. The method further includes forming a second dovetail slot having a second axial length within a portion of the rotating element. The second dovetail slot is substantially parallel to the axial centerline of the rotating element. At least a portion of the second dovetail slot is radially outboard of at least a portion of the first dovetail slot. The first axial length is greater than the second axial length. The method also includes enclosing at least a portion of the rotating element within at least a portion of a casing.

Abstract: A compressor wheel (7) is disclosed comprising an array of blades (20) extending from central hub (21) adapted from attachment to a rotatable shaft (8) and a backface (25). A region of the surface of the compressor wheel backface (25) is formed with a layer of residual compressive stress (26, 27).

Abstract: An annulus filler for mounting to a rotor disc of a gas turbine engine is provided to bridge the gap between adjacent blades. A first part is connectable to the rotor disc between adjacent blades. There is a separate second part that engages with the first part after connecting the rotor blades to the rotor disc. When installed, the filler is spaced from each blade by a respective clearance gap (G), and an operational configuration in which it contacts each of said blades. Engagement of the second part with the first part is effective to urge the first part from said installation configuration to said operational configuration and thus into blade contact. The first part may have a mounting region for connection to the rotor disc and allow, in said first step of said procedure, the mounting region to remain visible from a radially outer viewpoint.

Abstract: A method of manufacturing an impeller of a centrifugal rotary machine, the impeller being formed in a substantially disk shape and including a passageway curved to follow the axial direction in an inner peripheral side of the impeller and to follow the radial direction as it goes to an outer peripheral side thereof, the method includes: a first passageway forming step of setting a rotation center at a position on one side of the axial direction where a curvature center of the passageway is located relative to a disk forming an external shape of the impeller, and rotating a processing tool about the rotation center relative to the disk so as to form at least a part of the passageway from a position which is an inner peripheral end of the passageway of the disk toward the outer peripheral side.

Abstract: A retaining system is provided for circumferential entry rotor dovetails inserted into dovetail slot in a rotor. A plurality of rotor blade dovetails are circumferentially slidable into and along the dovetail slot, with each rotor blade dovetail having a neck and a pair of oppositely oriented lobes. A plurality of rail segments are circumferentially slid into channels in the dovetail slot between the dovetail lobes and the respective disk hoops. The rail segments define a first pressure face that engages against an outward pressure face of the dovetail lobes, and a second pressure face that engages against an inward pressure face of the respective disk hoop component.

Abstract: A rotor stack is assembled to a turbine engine shaft. A force is exerted to at least one of the rotor stack and the shaft to at least one of place the shaft under tension and place the rotor stack under compression. One or more retainer segments are inserted into a rebate in the shaft. The exerted force is released to permit the rotor stack to bear against the retainer segments.

Abstract: A method and an assembly for fastening at least one screw nut to be tightened of a rotor blade bearing of a wind turbine are provided. A screw nut driver assembly is provided at a rotatable portion of the rotor blade bearing, the screw nut driver assembly being adapted to automatically tighten the at least one screw nut. The screw nut driver assembly is aligned with the screw nut to be tightened by rotating the rotatable portion with a pitch drive of the wind turbine. Then the screw nut is tightened using the screw nut driver assembly.

Abstract: An apparatus enables a turbine nozzle, including at least two turbine nozzle singlets to be fabricated. Each singlet includes inner and outer bands and a vane extending therebetween. The vane also includes first and second sidewalls coupled together at a leading edge and a trailing edge. The apparatus comprises a fixture, and at least two support members extending from the fixture. Each support member has first and second abutment surfaces, wherein a first of the at least two support members contacts at least one of the leading and trailing edges of a first of the vanes. At least two locating features extend from the fixture, wherein a first of the locating features contacts one of the first and second sidewalls of the first vane. At least two biasing members are coupled to the fixture, wherein a first of the biasing members biases the first vane against the first locating feature.

Abstract: A method for sealing a gas turbine engine includes coupling a turbine bucket to a rotor wheel and forming an interface region therebetween. A cooling air passage is defined in a portion of the rotor wheel and a cooling air manifold is defined in a portion of the turbine bucket. The method also includes inserting a seal tube within at least a portion of the cooling air passage. The method further includes coupling the cooling air passage, the seal tube, and the cooling air manifold in flow communication to at least partially define a turbine bucket cooling system. The method also includes operating the gas turbine engine such that the rotor wheel and the turbine bucket are rotated, thereby inducing a pressure on the seal tube to substantially decrease air flow discharged from the turbine bucket cooling system through the interface region.

Abstract: A gas turbine engine includes a radial compressor having first and second blades. The first blade has a tuned leading edge that prevents either blade from exciting at a natural frequency at speeds within an expected operating speed range.

Abstract: A gas turbine engine includes a radial compressor with first and second blades. The first and second blades have tuned leading edges that prevent natural frequencies from exciting at speeds within an expected operating speed range.

Abstract: The invention relates to a Pelton turbine that comprises a plurality of sub-assemblies arranged about the rotation axis of the wheel and each including a bucket (111) and an anchoring leg (112). At least one blocking pin (13) is provided in a direction (X13) parallel to the rotation axis (X1) of the wheel between two adjacent anchoring legs (112, 112?), wherein said pin is inserted into two housings (1126, 1127) respectively formed in the two anchoring legs (112, 112?). According to the method of the invention, the blocking pin (13) is placed by inserting the same into the two housings (1126, 1127) of two adjacent anchoring legs (112, 112?). The pins are placed into the housings with a clearance, thereby allowing the relative sliding of the anchoring legs (112, 112?) before blocking them with the pins (13).

Abstract: Disclosed is a rotor assembly for a turbomachine includes a disk having a first axial face and a second axial face. The disk includes at least one circumferential dovetail extending around an outer surface of the disk and a plurality of axial dovetails extending from the first axial face to the second axial face. Each blade of a plurality of blades is installed into an axial dovetail of the plurality of axial dovetails and each platform of a plurality of platforms is installed adjacent to a blade of the plurality of blades via the at least one circumferential dovetail. Further disclosed is a method of assembly of a rotor for a turbomachine.

Abstract: A seal assembly for a gas turbine engine including a seal member and an interstage seal ring including an axially forward member coupled to a first radially inward surface of a first disk and an axially aft member coupled to a second radially inward surface of a second disk, wherein the seal ring is configured to move in an axial direction while the upstream and downstream arms are coupled to the first and second disk respectively.

Abstract: A stator vane that may be used in an engine assembly is provided. The stator vane includes an airfoil that has a first sidewall and a second sidewall, which connects to the first sidewall at a leading edge and at a trailing edge. The airfoil also includes a root portion and a tip portion. The first and second sidewalls both extend from the root portion to the tip portion. The airfoil root portion is formed with a negative lean, and the airfoil tip portion is formed with a positive lean.

Abstract: A nose cone assembly for a gas turbine engine is disclosed herein. The nose cone assembly includes a spinner body having an outer surface and extending axially between an upstream portion generally tapering to a truncated first end and a base portion generally cylindrical in cross-section at a second end. The nose cone assembly also includes a flange positioned radially inward of the outer surface and axially adjacent to the base portion. The nose cone assembly also includes a plurality of first apertures defined in the flange for removably connecting the spinner body to a fan of a gas turbine engine. The nose cone assembly also includes a second aperture defined in the spinner body through which all of the plurality of first apertures can be accessed for attaching or removing the nose cone assembly from the fan.

Abstract: A process for manufacturing an integrally bladed disk for a turbomachine rotor by friction welding is disclosed. The manufacturing process includes arranging a plurality of blades in the form of a ring in a mold having symmetry of revolution; casting a degradable material, preheated to a temperature above its melting point, onto the ring of blades in the mold; extracting the molded ring which is obtained after the degradable material has solidified; welding the molded ring onto a disk; and eliminating the degradable material.

Abstract: Method for manufacturing a stator component or rotor component (10) including at least one ring element (3). A joining material is provided in contact with at least one of the blade (2) and the ring element (3). The blade and the ring element are arranged in relation to one another in such a way that they are joined together via a butt joint when heated, and when such heat-treatment is subsequently carried out, the joining material forms a melt that joins the parts together upon solidification.

Abstract: A fixture assembly for securely positioning a plurality of blades loosely assembled on to a rotor of a gas turbine engine in which axial clamping forces are translated to apply radial expansion forces on the blades to simulate a centrifugal force on the blades during engine operation.

Abstract: A method of replacing an individual damaged compressor stator airfoil includes machining an oversized slot through the stator casing, removing the damaged airfoil, and joining a sleeve to the replacement airfoil and stator casing. The oversized slot creates sufficient clearance for removal of a three-dimensional airfoil, while the sleeve creates a sufficiently tight fit to allow the pieces to be brazed together.

Abstract: A process for machining axial blade slots in turbine disks used in jet engines is provided. The process broadly includes the steps of providing a turbine disk, forming a roughened slot having a plurality of joined rectangular areas in the turbine disk, and machining the roughened slot to a finished slot.

Abstract: The invention relates to a fitting device for producing the arrangement for locking a sealing element, arranged at the front end on a rotor of a turbine, against a displacement in the circumferential direction, the sealing element locking moving blades arranged on the rotor against an axial displacement. Furthermore, the invention comprises a method of producing the arrangement for locking a sealing element, arranged at the front end on a rotor of a turbine, against a displacement in the circumferential direction. The quality of the fitting can be further increased by means of a modular, mobile fitting device which secures the sealing element for the duration of the bending operation.

Abstract: A turbine blade assembly, which can be used for a gas turbine is provided. The turbine blade assembly includes turbine blades with platforms, gaps between the platforms of adjacent turbine blades and seals. Each seal covers the gap between the platforms of two adjacent turbine blades wherein the platforms are provided with slots extending in the downstream flow direction. The turbine blades have root cavities, wherein the seal covers at least the whole length of the root cavities of two adjacent turbine blades. The seal is formed from a strip and the seal is placed in two opposed slots formed in each of the platforms of two adjacent turbine blades and open towards the respective downstream ends.

Abstract: One embodiment is an apparatus comprising a first rotational gas turbine engine component including first threads; a second rotational gas turbine engine component including second threads; the first threads and the second threads being mated; and the first rotational engine component being fastened to the second rotational engine component substantially only by the first threads and the second threads being mated. Other embodiments include unique apparatuses, systems, devices, and methods relating to gas turbine engine interconnection. Further exemplary embodiments, forms, objects, features, advantages, aspects, and benefits of the present invention are included in the following description, drawings, and claims.

Abstract: Stator blade counts of an upper compressor casing for adjacent stages S0 and S1 are changed in the field to provide additional stator vanes and hence an increased vane count. Particularly, the upper casing half of the compressor is removed from the lower casing half. The original stator vanes on opposite axial sides of the first stage buckets are removed from the upper casing half and replaced by an additional sets of stator vanes providing a non-uniform vane spacing as between the upper and lower halves of the compressor as well as between axially adjacent stages S0 and S1. The unequal vane counts reduce the vibratory response of the rotating blades between stages S0 and S1.

Abstract: A blade module of a modular rotor blade comprising a hollow fiber composite body which extends along a longitudinal blade axis and at least one inlay located at or near a longitudinal end of the fiber composite body is provided. The inlay includes a receptacle which is adapted to receive a threaded fastener and an anchoring portion anchored to the fiber composite body. Further, a modular wind turbine rotor blade which includes at least two blade modules and a method for assembling a modular wind turbine rotor blade are provided.

Abstract: A method for repairing a wind turbine is described. The method may include preparing the surface of the blade, removing a plurality of mounting bolts, and replacing the mounting bolts with rod members. The rod members may be bonded to the blade root thereby strengthening the blade root and/or repairing any damaged or weakened regions. This repair may be performed on blades and blade coupling regions of various characteristics as well in modular fashion using pre-molded sections attached together around the blade root. The method of repair may be performed while the blade is still attached to the turbine hub. Wind turbines repaired according to these methods are also described. The method may also be used for attaching and otherwise handling new turbine blades and new wind turbines.

Abstract: A compressor drum for an axial turbo-machine includes a hollow body generally symmetrical in revolution about its axis of rotation and forming a shell at the periphery of which are arranged a plurality of parallel rows of vanes, each row corresponding to one stage of the compressor. Each vane includes at its root an attachment platform housed in a corresponding opening made in the shell of the hollow body. The outer surface of each platform is flush with the outer surface of the shell at the edge of the opening and each platform is attached to the hollow body by welding between the outer edge of the platform and the inner edge of the corresponding opening. The platform has the general shape of a parallelogram, a bisector of which corresponds approximately to the main axis of the profile of the vane at the platform.

Abstract: A rotor for a gas turbine engine having a stub shaft and an axis of rotation, the rotor including a turbine hub clamped to a coaxial tie shaft with a tie shaft nut, the stub shaft comprising: a hollow stub shaft body extending rearwardly axially of the turbine; a forward portion of the stub shaft body disposed radially outwardly of the tie shaft nut and removably mounted to a rearward portion of the turbine; and a rearward portion of the stub shaft body including an inner bearing race mounting surface.

Abstract: A process for joining a turbine wheel and a turbine shaft of a turbocharger comprising the steps of: providing a turbine wheel; providing a turbine shaft; holding the turbine shaft in a welding device; contacting the turbine shaft to the turbine wheel; energizing a pilot current; lifting the shaft a predetermined height from the turbine wheel to draw a pilot arc; energizing a weld arc current locally melting the shaft weld end and forming a weld pool on the wheel; plunging the shaft toward the wheel into the weld pool; turning off the current; and removing the welding device from the welded shaft.

Abstract: An elastomer material seal for an interleaved platform between two adjacent blades in a turbomachine rotor is disclosed. The seal is of elongate shape and includes transversely a contact part, an attachment part, and a flexible part between the attachment part and the contact part. The seal is noteworthy in that it further includes a local reinforcement of the flexible part, to avoid the tearing that would result from centrifugal forces on the seal. The local reinforcement of the flexible part includes at least one transverse rib on the flexible part.

Abstract: An airfoil has a hollow shell providing external airfoil surfaces, and a corrugated core within the shell. The core contacts inner surfaces of the shell to support the shell. The airfoil is formed by consolidating a hollow shell pre-form and a corrugated core pre-form. At least a part of the hollow shell has a leading edge shell portion and/or a trailing edge shell portion which, before consolidation of the pre-forms, is a unitary body having a shape which wraps around the respective edge.

Abstract: A wheel is constructed from a disk disposed for rotation about an axis and a ring with a plurality of blades being connectable to the disk. The wheel is operable for pumping, compressing, or expanding fluid in a turbomachine. The disk is configured to receive at least a portion of the ring within the disk and be coupled using a protrusion or protrusions. The protrusion can be configured to prevent relative movement between the disk and the ring. In some forms a bracket can be extended between the ring and disk to prevent relative movement.

Abstract: A method of fabricating or reparing a blisk (10) that comprises a plurality of blades (14) attached to the outer periphery of a disc (12). Blades (14) are formed separately from the disc (12) and are attached to stubs (13) on the disc (12) by friction welding. A metal powder, such as titanium, is sprayed onto the stubs (13) to reinforce them during the friction welding process. Once the stub (13) has been coated with the powder spray, plates (20) are fastened on the disc (12) between which the sprayed coating (18) is clamped. The plates (20) restrain the sprayed coating (18) to prevent delamination during friction welding. Once each of the blades (14) has been welded onto the respective stubs (13) the clamping plates (20) are removed and the sprayed coating (18) is machined away.

Abstract: A machining system includes a support configured to retain an article, such as a rotor disk, having an area, such as a surface of a slot in the disk. A cutting tool, for example, a broach, is movable relative to the support to cut the area. A heating member, such as a laser, is configured to locally heat the area of the article. In one example, the cutting tool includes a body having a cutting edge. The heating member is supported by the body and is configured to provide heat adjacent to the cutting edge. The cutting edge cuts the locally heated area while the area is still heated.

Abstract: A method and an assembly for fastening at least one screw nut to be tightened of a rotor blade bearing of a wind turbine are provided. A screw nut driver assembly is provided at a rotatable portion of the rotor blade bearing, the screw nut driver assembly being adapted to automatically tighten the at least one screw nut. The screw nut driver assembly is aligned with the screw nut to be tightened by rotating the rotatable portion with a pitch drive of the wind turbine. Then the screw nut is tightened using the screw nut driver assembly.

Abstract: A turbomachine includes a turbine stage having a plurality of blades including a first and a second blade disposed adjacent to each other, each blade having a radial longitudinal axis and a blade tip and configured to twist around the radial longitudinal axis in an operating state in a twist direction, wherein the first and the second blades are pretwisted in a direction of twist in a non-operating state, and wherein a connecting element interconnects the first and the second blades to each other in a circumferential direction in a region of the respective blade tip so as to maintain the pretwisting.

Abstract: A method of fixturing a plurality of dissimilar blade assemblies, wherein each assembly undergoes one or more manufacturing steps to bring it to a finished form, the method comprising the step of providing on each of the articles a datum feature, wherein each datum feature is of identical form and dimension, in turn a) locating the datum feature of a first one of the articles in a complimentary fixture to secure the dissimilar article, b) performing at least one manufacturing step on the secured dissimilar article, c) removing the dissimilar article from the fixture, d) locating the datum feature of another of the articles in the complimentary fixture to secure the dissimilar article, e) performing at least one manufacturing step on the secured dissimilar article, f) removing the dissimilar article from the fixture.

Abstract: An outer seal assembly of a turbine rotor stage is secured within a circumferential groove of the turbine casing in such a manner as to both fix the outer seal assembly in its installed position and also provide for sealing around its outer periphery so as to thereby prevent the leakage of cooling air therearound. A plurality of arcuate elements having an angle-shaped cross sectional profile are provided to interface between radially extending arms of the outer seal assembly and the inner surface of the casing, with a locking mechanism then being applied to secure the two structures in their installed positions. Each of the arcuate elements includes a radially extending panel, a plurality of forwardly extending hooks that are disposed within a groove in the casing, and a second forwardly extending flange that engages the rear surface of the outer seal assembly arm.

Abstract: A method includes joining an integral bulkhead and a blade shell to form a blade and separating the blade into two blade segments at a location including the integral bulkhead such that each blade segment comprises a portion of the integral bulkhead and a portion of the blade shell.

Abstract: A blade attachment apparatus for a turbine is provided and includes a member, which rotates about an axis of the turbine, including fore and aft disk posts that retain corresponding fore and aft turbine blades, respectively, fore and aft of a turbine nozzle and a central portion proximate the turbine nozzle and an attachment retained between the fore and aft disk posts and the fore and aft turbine blades and coupled to the central portion, such that a portion of the attachment interrupts a purge flow through the turbine.

Abstract: A turbine blade is disclosed. The turbine blade may have an airfoil extending from a first surface of a turbine platform. The turbine blade may further have a first side pocket of the turbine platform that is configured to substantially entirely house a first moveable seal between a forward wall of the first side pocket and an aft wall of the first side pocket. The first side pocket may have a convex surface, extending between the forward wall and the aft wall, and a concave surface. The turbine blade may also have a second side pocket of the turbine platform configured to receive a portion of a second moveable seal.

Abstract: A variable nozzle device including an annular nozzle passage formed by a gap between two opposing wall members and at least one vane rotatably supported in the nozzle passage. The vane is formed by a strip of sheet metal contoured to have an outer aerodynamic profile, and having a hollow interior with surfaces mimicking the outer profile. The vane is affixed to a shaft having a wind-stream portion forming two contact surfaces that conformingly receive opposing portions of the interior surfaces.

Abstract: A method enables rotor assembly for a gas turbine engine to be assembled. The method includes providing a plurality of rotor blades that each include a dovetail, providing a rotor disc that includes a plurality of dovetail slots spaced circumferentially about the disc, partially inserting each rotor blade dovetail into a respective rotor dovetail slot, and seating the plurality of rotor blades in the respective rotor dovetail slot substantially simultaneously using an annular blade installation tool.

Abstract: A method of assembling a rotor assembly is provided. The method comprises forming at least one channel in a dovetail portion of at least one rotor blade assembly, wherein the rotor blade assembly includes an airfoil extending outwardly from the dovetail portion, inserting a sealing assembly within the at least one channel of the dovetail portion, and coupling the at least one rotor blade assembly to a rotor disk using the dovetail portion such that at least a portion of the sealing assembly is between the dovetail portion and the rotor disk.