Abstract: A method and apparatus for improving fan case containment in a gas turbine jet engine employs a containment ring and a heat resistance ring which are shrink interference fit on the inside diameter of the fan case, the containment ring where the large fan blades turn, and the heat resistance ring where heated air from backfiring heats up the fan case. The containment ring is made of a super alloy to provide added strength to the fan case should a fan blade break, containing the fan blade within the fan case. The heat resistance ring is made of titanium or other suitable material. Additionally, one or more stiffener rings are shrink interference fit on the outside diameter of the fan case. The containment ring and stiffener rings can reduce the flight weight of the fan case and lower the material costs, while increasing the containment strength of the fan case.

Abstract: A variable geometry turbine comprises a turbine wheel mounted within a housing for rotation about a turbine axis; and a gas flow control passage upstream of said turbine wheel, the gas flow control passage being defined at least in part between a radial first surface of a movable wall member and a facing wall of the housing, the movable wall member also comprising second and third surfaces which oppose the first surface. The movable wall member is movable in an axial direction so as to vary the size of the gas flow control passage. There is a first gas region of the turbine, a portion of which is upstream of the gas flow control passage, the first gas region including at least a portion of the gas flow control passage; a second gas region of the turbine downstream of the gas flow control passage which contains the turbine wheel; and a third gas region of the turbine downstream of the turbine wheel.

Abstract: Embodiments of the present disclosure relate to a turbine which includes an outer shell, an inner shell connected to and surrounded by the outer shell in generally concentric relation therewith, at least one turbine rotor housed within the inner shell, a plurality of nozzles and shrouds carried by the inner shell, a plurality of connecting elements engaging between the inner and outer shells aligning the inner shell about the rotor, and at least one compliant support. Embodiments of the present disclosure also relates a method of configuring the securing arrangement between the inner shell and the outer shell of a turbine.

Abstract: A method for optimizing the mass of a composite panel composed of a plurality of uniform thickness zones, each zone defined by a vertical arrangement of plies, each arrangement having a different number of piles, and different orientation angles, where a positioning order of the plies has a given orientation angle with respect to the others in the vertical arrangement, and the proportion of plies has a given orientation angle with respect to all the plies composing the vertical arrangement. The optimization includes defining a lay-up table, and defining a vertical arrangement of plies for each uniform thickness zone, and starting from the lay-up table, building a function describing the physical properties of each zone as a function of the total thickness of each zone, where the total thickness for each zone is adjusted using a discrete variables iteration process, until the mass of the panel is a minimum.

Abstract: A system for forming a labyrinth seal on a turbine blade has a fixture with a plurality of nozzles for distributing a coolant, a first jaw set for clamping and holding a root portion of the turbine blade in a first orientation, which first jaw set is attached to the fixture and has two members for mating with said root portion of said turbine blade, each of the jaw set members respectively have ridges; and a plurality of grinding wheels for forming the labyrinth seal.

Abstract: A one-piece air exit port baffle for containment for an air start turbine includes a circular arc section with a circumferentially corrugated circular arc section and a flange section. The circumferentially corrugated circular arc section has a plurality of openings. The flange section is axially adjacent to the circumferentially corrugated circular arc section and configured for attachment adjacent to an air exit port of an air turbine starter.

Abstract: In the manufacture of integrally designed rotor wheels (BLISKs), the natural frequency of each blade is measured after forming by conventional shaping methods and the respective blade mass and its divergence from the smallest blade mass is calculated therefrom. The mass of each blade exceeding the smallest blade mass is removed by means of an etchant, so that all blades have essentially corresponding thickness, chord length, mass and natural frequency and are evenly loaded in operation. BLISKs manufactured in this way feature a long service life.

Abstract: An assembly used in performing a manufacturing process on a turbine engine component includes a turbine engine component and a fixture including an opening shaped to receive a portion of the turbine engine component. The assembly includes a non-metallic cover placed over at least a portion of an external surface of the fixture. The non-metallic cover is visible when positioned over the at least a portion of the external surface of the fixture and is visible when the turbine engine component is received in the fixture opening of the fixture.

Abstract: A moving fluid energy recovery system for generating electricity through rotational motion produced by positioning the present invention in a fluid flow produced by nature or a moving vehicle. The moving fluid energy recovery system has first and second end plates, a plurality of elongated inner vanes, a plurality of elongated outer vanes, and shaft to drive an electricity generating device. The inner and outer vanes each have a substantially curved profile featuring a curve side and an open side. The first and second end plates each has a central bore defined therethrough, a plurality of inner vane slots each shaped to receive a corresponding inner vane, and a plurality of outer vane slots each shaped to receive a corresponding outer vane. The inner vane slots are orientated with the curve side toward the central bore, and the outer vane slots are orientated with the open side toward the central bore with the free ends of adjacent inner vanes positioned in the open side of the outer vane slots.

Abstract: A turbine bucket includes an airfoil portion and a tip shroud at a radially outer end of the airfoil portion. The tip shroud includes a first radially inner tip shroud component formed integrally with the airfoil portion and composed of a first metal material, and a second radially outer structural tip shroud component composed of a second metal material bonded to the first radially inner tip shroud component.

Abstract: An assembly includes a fixture including an opening shaped to receive a portion of a turbine engine component. A non-metallic cover is placed over at least a portion of the fixture. The cover facilitates reducing metal to metal contact of the fixture and the turbine engine component when the turbine engine component is installed in the fixture, and facilitates reducing scratching of the turbine engine component.

Abstract: In one embodiment, a steam turbine rotor has a first and a second rotor, a first and a second flange, a bolt, and a cap nut. The first flange is connected to an end portion of a first shaft of the first rotor and has a first through hole. The second flange is connected to an end portion of a second shaft of the second rotor and has a second through hole. The bolt is inserted through the first and second through holes and has a shaft part, a male screw part disposed on one end of the shaft part, and a projection part disposed on an end portion of the male screw part. The cap nut has a female screw part engaged with the male screw part and a projection through hole which the projection part penetrates.

Abstract: An assembly including a metal piece, a piece made of ceramic material, and at least one intermediate connection element assembled to each of the pieces by brazing. The intermediate connection element includes a deformable sheet presenting at least two flat zones brazed to respective ones of the pieces, the two flat zones being interconnected by a deformable zone presenting at least two free undulations oriented in alternation towards the metal piece and towards the piece made of ceramic material.

Abstract: A rotor assembly for use with a turbine engine. The rotor assembly includes at least one rotor disk that includes an inner surface that defines a dovetail groove. At least one turbine bucket is coupled to the rotor disk. The turbine bucket includes an airfoil that extends outwardly from a dovetail. The dovetail is inserted at least partially within the dovetail groove. A tang assembly extends from one of the inner surface of the rotor disk and the dovetail. the tang assembly minimizes a rotation of the turbine bucket with respect to the rotor disk.

Abstract: A turbomachine includes a housing, and a plurality of turbomachine nozzles. At least one of the plurality of turbomachine nozzles includes a body having a first surface and an opposing second surface that extend between a first end and a second end. At least one of the first and second surfaces includes a profile having an angle of between about 3° and about 8° between a first line passing through the first end and a first position located between about 28% and about 38% from the first end and a second line passing through the first position and a second position located between about 53% and about 63% from the first end, and an angle of between about 10° and about 20° between the second line and a third line passing through the second position and a third position located between about 74% and about 84% from the first end.

Abstract: A method of forming a rotor for a turbine engine such that the rotor is formed of two materials including: an inner disk formed from a first material, such as steel, and an outer ring formed from a second material, such as a nickel alloy, having a larger thermal expansion coefficient than the first material forming the inner disk. The ring may include an inner aperture having a conical shape, and the disk may have an outer surface with a conical shape and a diameter with a portion that is larger than a portion of the ring. The ring may be heated such that the aperture expands to a size greater than the largest diameter of the inner disk. The ring may be positioned over the disk and allowed to cool to allow the ring to be attached to the disk. The ring and disk may then be co-forged.

Abstract: A shroud segment for a turbine stage of a gas turbine engine forms an endwall for the working gas annulus of the stage. The segment also provides a close clearance to the tips of a row of turbine blades which sweep across the segment. In use, a mainstream flow of the working gas passes through the passages formed between adjacent turbine blades. The segment has a plurality of cooling holes and respective air feed passages for the cooling holes. The cooling holes are distributed over that part of the gas-washed surface of the segment which is swept by the blade tips. The cooling holes deliver, in use, cooling air which spreads over the gas-washed surface. The feed passages are configured such that the delivered air has swirl directions which are co-directionally aligned with the swirl directions of the mainstream flow at the segment.

Abstract: A turbine rotor with a rotor disc, a plurality of slots arranged on the rotor disc, a plurality of blades having blade roots and arranged in the slots, and a plurality of locking plates fitted in a position between the rotor disc and the blades are provided. The first gaps on radially outside edges and second gaps on radially inside edges, relative to an axis of rotation of the rotor disc, are formed between neighboring locking plates. At least one of the first gaps is smaller than the corresponding second gap, wherein at least one first gap and corresponding second gaps are intentionally introduced.

Abstract: A premix burner is provided for a gas turbine, in the form of a double-cone burner, which has two partial cone shells which are arranged nested one inside the other, forming air inlet ducts between them, through which combustion air from the outside flows into a conical inner space of the premix burner. Linear rows of holes of injection openings, which extend transversely to the flow direction of the combustion air, are arranged on the outer walls of the air inlet ducts and through which a gaseous fuel is injected into the combustion air which flows past transversely to them. A method for reworking such premix burners is also provided.

Abstract: Method, system and axial multistage expander including a casing and a plurality of stages. A stage includes a stator part connected to the casing and having plural statoric airfoils, and a rotor part configured to rotate relative to the stator part and having plural rotoric airfoils. The axial multistage expander also includes a support mechanism connected to the casing and configured to rotatably support the rotor part. Rotoric airfoils of at least one stage of the plurality of stages are configured to rotate with a speed different from rotoric airfoils of the other stages. The stator part, the rotor part and the support mechanism of the plurality of stages are provided inside the casing.

Abstract: A vane profile section for an Air Turbine Starter includes an airfoil which defines an airfoil profile section through a leading edge and a trailing edge, the airfoil profile section defined by a set of X-coordinates and Y-coordinates.

Abstract: A blade profile section for an Air Turbine Starter includes an airfoil which defines an airfoil profile section through a leading edge and a trailing edge. The airfoil profile section is defined by a set of X-coordinates and Y-coordinates defined in any of Table I, Table II, Table III or Table IV scaled by a desired factor. The X-coordinate is the tangential direction, the Y-coordinate is the axial direction, and the Z-coordinate is a radial direction between an airfoil root and an airfoil tip.

Abstract: An inlet housing assembly for an Air Turbine Starter includes an outer flowpath curve of an inlet flowpath defined by a multiple of arcuate surfaces in cross-section.

Abstract: An actuator has a rotary drive and a threaded element for converting the rotary motion of the rotary drive into a reciprocating motion of a tappet connected to a hinged wastegate and/or to a variable turbine geometry device of an exhaust gas turbocharger. The tappet and/or an axle between the tappet and the threaded element is received in at least one guide comprising at least one web and allowing for at least a slight tilting or pivoting movement of the tappet in at least one direction. At least some play is present between the web and at least one broadened portion on the tappet and/or on the axle. Methods of actuating a wastegate and/or a variable turbine geometry device.

Abstract: A disk spacer for a gas turbine engine includes a rim, a bore, a web and a load path spacer. The web extends between the rim and the bore. The load path spacer is positioned between the rim and the bore.

Abstract: A receptor assembly for lightning protection of an object, such as a wind turbine blade, includes a receptor disk configured to be placed on a surface of the object, a receptor block insulator with an integral receptor block, a cover that engages the receptor block insulator, and a cap that engages the cover. The receptor disk and the receptor block may be made of electrically conductive materials, and the cover, and the cap, and the receptor block insulator may define a chamber among them that is lined with an electrically-conductive coating sandwiched between relatively high dielectric media to electrically isolate and shield internal parts of the receptor assembly from receiving a lightning strike directly.

Abstract: An airfoil root fillet having a predetermined compound curve profile can be flank milled with a single flank milling cutter having a generally conical flank milling portion and a rounded tip portion defining a compound curve.

Abstract: This invention relates to a method of lifting a wind turbine nacelle (1), the method comprising: arranging a first and second anchoring point (2,3) on each of two opposing sides of the nacelle (1), the first point (2) of each side being arranged below the center of gravity (4) of the nacelle (1) and the second point (3) of each side being arranged above the center of gravity (4), wherein one of said first and second anchoring point (2,3) of each side is immovably arranged, and wherein the other one of said first and second anchoring point (2,3) of each side is movably arranged; interconnecting said first and second anchoring point (2,3) on respective side of the nacelle (1) by means of one connecting element (5) per each of the two sides; connecting each of said connecting elements (5) to a hoisting means (11); adjusting the position of each of the movable anchoring points such that each of the connecting elements (5) is vertically aligned when lifting the nacelle (1) by the hoisting means (11).

Abstract: A wind turbine apparatus includes a unit structure that is coupled to a central hub by way of an in-tension cable. The unit structure includes a first set of struts, wherein each strut in the first set of struts includes first and second ends, the first ends of the first set of struts are coupled to a first node and the first set of struts extend from the first node towards the central hub. The unit structure also includes a second set of struts, wherein each strut in the second set of struts includes first and second ends, the first ends of the second set of struts are coupled to the first node and the second set of struts extend from the first node away from the central hub.

Abstract: A turbine nozzle is provided and includes a first ring having a first microstructure, a vane extending from the first ring, a first porous zone between the first ring and the vane that is more porous than the first microstructure to attenuate thermo-mechanical fatigue cracking between the vane and the first ring. Methods of manufacturing the turbine nozzle are also provided.

Abstract: A method for assembling a rotating machine includes providing a rotating element including a plurality of rotor wheels. The method also includes positioning the rotating element such that at least a portion of a stationary portion extends at least partially about the rotating element. The method further includes assembling an interstage seal mechanism including coupling at least a portion of a first hook device to the rotating element, and also including coupling at least a portion of a second hook device to the first hook device. The first hook device and the second hook device are radially inboard of at least a portion of the stationary portion.

Abstract: A method for assembling an additive injection system for use with a turbine engine includes coupling an atomizing air connection to a fuel nozzle assembly and coupling an additive source to the atomizing air connection.

Abstract: A gas turbine engine rotor tip clearance and shaft dynamics system and method are provided. The system includes a gas turbine engine that is disposed within an engine case and includes a rotor. A rotor bearing assembly disposed within the engine case rotationally mounts the gas turbine engine rotor. Vibration isolators mounted on the engine case are coupled to the rotor bearing assembly, and are configured to provide linear and independently tunable stiffness and damping. A method includes determining the location of a gas turbine engine rotor rotational axis, disposing the gas turbine engine rotor in an engine case at the rotational axis location, mounting a plurality of vibration isolators that include a plurality of adjustment devices on the engine case, coupling each vibration isolator to the gas turbine engine rotor, and locking the gas turbine engine rotor at the rotational axis location using the plurality of adjustment devices.

Abstract: A method for assembling an additive injection system for use with a turbine engine includes coupling a liquid fuel connection in flow communication with a water supply manifold and coupling an additive source in flow communication with the water supply manifold.

Abstract: A film cooling structure formed in a component wall of a turbine engine and a method of making the film cooling structure. The film cooling structure includes a plurality of individual diffusion sections formed in the wall, each diffusions section including a single cooling passage for directing cooling air toward a protuberance of a wall defining the diffusion section. The film cooling structure may be formed with a masking template including apertures defining shapes of a plurality of to-be-formed diffusion sections in the wall. A masking material can be applied to the wall into the apertures in the masking template so as to block outlets of cooling passages exposed through the apertures. The masking template can be removed and a material may be applied on the outer surface of the wall such that the material defines the diffusion sections once the masking material is removed.

Abstract: A method is provided of rotationally balancing a rotating part. A rotor hub or ring and a plurality of rotor blades for assembly onto the hub or ring are provided, each blade having an unfilled internal cavity. The respective masses and moment weights of the blades with filled internal cavities are then predicted. Next, the rotor blades are assembled onto the hub or ring to form the rotating part. The relative positions of the assembled blades are determined on the basis of their predicted masses and moment weights with filled internal cavities. The internal cavities of the assembled rotor blades are then filled.

Abstract: Multi-component vane segment and method for forming the same. Assembly includes: positioning a pre-formed airfoil component (12) and a preformed shroud heat resistant material (18) in a mold, wherein the airfoil component (12) and the shroud heat resistant material (18) each comprises an interlocking feature (24); preheating the mold; introducing molten structural material (46) into the mold; and solidifying the molten structural material such that it interlocks the pre-formed airfoil component (12) with respect to the preformed shroud heat resistant material (18) and is effective to provide structural support for the shroud heat resistant material (18). Surfaces between the airfoil component (12) and the structural material (46), between the airfoil component (12) and the shroud heat resistant material (18), and between the shroud heat resistant material (18) and the structural material (46) are free of metallurgical bonds.

Abstract: A variable-pitch vane for a stator stage including includes an active part of the vane either side of which are positioned a radially inner platform and a radially outer platform, where the active part of the vane, which has a surface forming a convex surface, and a surface forming a concave surface, separate the platform into a part positioned on the convex side and a part positioned on the concave side. Seen along the direction of the vane's axis of rotation, the part has an outer outline superimposed on a circle, at the distance of which, and inside which, is at least a part of the outer outline of the part of the platform.

Abstract: A method of fabricating a turbomachine rotor disk is disclosed. In the method, a metal container is defined, made up of a plurality of parts that define between them at least one annular cavity, an insert made of composite material is positioned in the at least one cavity, the assembly is subjected to hot isostatic compacting, and a rotor disk is machined.

Abstract: An impeller assembly is for a fluid machine, such as a compressor, and includes a first, main body and a second body. The main body includes a first section providing at least a substantial portion of either an impeller disc or an impeller cover and a second section spaced generally axially from the first section and providing a portion of the other one of the disc or the cover. A plurality of integrally formed blades extend between and connect the main body first and second sections such that the main body is generally of one piece construction. A plurality of flow channels are defined between the blades and a plurality of access openings extend into the flow channels. The second body provides a remainder of the disc or cover and is attachable to the main body to substantially form an impeller and to close all of the access openings.

Abstract: A method for fabricating a nozzle segment for use within a turbine nozzle assembly. The method comprises providing a nozzle segment including an outer band, an inner band, and at least one vane extending there between, wherein at least one of the inner band and the outer band is formed with a transition piece groove defined therein, positioning an inspection tool in contact with the nozzle assembly such that the inspection tool is aligned relative to the nozzle segment using at least one datum, and verifying an alignment of each transition piece groove using the inspection tool.

Abstract: A method for fabricating a brush seal assembly comprising, bending a first plate member to a helical shape, bending a second plate member to a helical shape, securing the first plate member to a drum, winding a wire material around the drum and the first plate member, securing the second plate member to the drum, attaching the second plate member and the first plate member to the wire, and cutting the wire to define a bristle length.

Abstract: A method and ground support equipment (GSE) for attaching an engine core to an engine fan module on an aircraft pylon. The GSE may comprise GSE supports and lifting components attached to the pylon, two suspension rails attached to the lifting components, two translating rails translatably attached to the two suspensions rails and fixedly attached to opposite sides of the engine core, and two alignment fittings fixed to the engine fan module. The method of using the GSE may comprise lifting the engine core vertically using the lifting components and anchoring the suspension rails to the alignment fittings. The translating rails and engine core may then be translated in an aft-to-forward direction such that portions of the translating rails engage portions of the alignment fittings to cooperatively guide the translating rails into a final forward position in which the engine core is aligned relative to the engine fan module.

Abstract: A fixture and method for assembling axial entry buckets with complex geometry to a rotor wheel is provided. The fixture features an inner and an outer split ring shaft clamp, which is bolted together around the rotor wheel packing diameter and provides a mounting base. The transfer ring mounts around and abutting the rotor wheel. The transfer ring includes a circumferential slot to accept bucket-holders. The bucket holders loaded with turbine buckets, inserted onto the transfer ring and moved circumferentially around the transfer ring to align the turbine buckets to slots on the rotor wheel. Pressure is applied to spiral the buckets from the bucket-holders into final position in slots on the rotor wheel.

Abstract: A method of repairing a turbomachine blisk having at least one damaged zone by build-up of metal in the damaged zone using a laser build-up welding machine is disclosed. The method includes preparing the damaged zone by machining the damaged zone to obtain a zone of defined profile to be repaired, build-up welding of a start-of-run test piece that includes the defined profile using the laser build-up welding machine, checking geometric and metallurgical quality of the test piece, and build-up welding the zone to be repaired of the blisk using the laser build-up welding machine.

Abstract: A gas turbine composite workpiece, such as a workpiece forming a part of a gas turbine casing, is provided. The workpiece includes at least two components joined by at least one weld seam. In order to reduce thermal stresses of the workpiece during operation, the weld seam is interrupted by at least one aperture. In order to reduce the exchange of gases between the workpiece's sides, the workpiece may be equipped with an arrangement for preventing gas flow through the aperture.

Abstract: A method for making a gas turbine component (100). A central core (20) is positioned to occupy a space that will define a central channel (42), and an outer channel core (30) is positioned spaced apart from the central core (20). A mold (35) is formed around the central core (20) and the outer channel core (30), so that an exterior wall (32) contacts the mold (35). A substrate material, such as a metal alloy (247) in liquid form, is added to the mold (35) to form an internal volume (41) of the component (100). The central core (20) and the outer channel core (30) are removed, and interconnect channels (44) are formed between the thus-formed central channel (42) and the inner portion (49) of the outer channel (62) thus far formed. A preform (55) is placed into the inner portion (49) and may have a desired outer surface (57) shape. An overlay material is applied to form an outer layer (60), thus defining the remainder of the outer channel (62), which is obtained upon removal of the preform (55).

Abstract: A device for heating a cylindrical component of given diameter is disclosed. The device includes at least two heaters each delivering a stream of hot gas and emerging in an annular chamber. The inside diameter of the annular chamber is slightly greater than the diameter of the cylindrical component. The device may be used for heating a metal journal in which a bearing ring for an inter-shaft bearing in a double-body turbomachine is mounted.

Abstract: A turbine that includes a rotor, an inner turbine shell, an outer turbine shell, and a sliding engagement between the inner turbine shell and the outer turbine shell. The inner turbine shell is a single piece construction that completely surrounds at least a portion of the rotor, and the outer turbine shell surrounds the inner turbine shell. A method for aligning turbine components that includes aligning a single-piece inner turbine shell substantially concentric with a rotor and surrounding the single-piece inner turbine shell with an outer turbine shell. The method further includes supporting the single-piece inner turbine shell with respect to the outer turbine shell using a bearing assembly between the single-piece inner turbine shell and the outer turbine shell.

Abstract: An abradable seal for a gas turbine engine includes a metal alloy and a plurality of pores in the metal alloy. The plurality of pores have a diameter of approximately 1 to 10 microns.