Abstract: A method of manufacturing a turbine engine component comprising the steps of providing and laying up a plurality of ceramic plies comprising woven ceramic fiber tows to form a turbine engine component shape, inserting a plurality of tows of oxidizable fugitive fibers into the component shape, such that each fugitive fiber tow passes through a preselected number of ceramic plies, burning off the fugitive fiber tows, the burning producing through-thickness void regions, rigidizing the component shape with a layer of BN and a layer of SiC to form a coated component preform using chemical vapor infiltration, and partially densifying the coated component preform using carbon-containing slurry and filling the through thickness void regions, and further densifying the coated component preform with at least silicon to form a ceramic matrix composite turbine engine component with in-situ ceramic matrix plugs formed where the through-thickness void regions were located.

Abstract: Composite containment casing including a body having an interior, an abradable system integrally joined to the interior of the body of the containment casing wherein the abradable system comprises, a sandwich structure including a first facesheet and a second facesheet position about at least one core layer, and at least one abradable layer applied to the sandwich structure wherein the at least one core layer comprises any of a cell configuration, a columnar configuration, or a truss configuration and wherein the sandwich structure is strong radially and weak circumferentially.

Abstract: A Ni-based alloy member has resistance against grain boundary fracture, fatigue strength, and oxidation resistance at temperatures near 1000° C. or higher. The Ni-based alloy member includes a non-repaired region made of a Ni-based alloy base and a region repaired by welding, which is formed on the non-repaired region and which is made of a buildup-welded layer, the buildup-welded layer being made of a Ni-based alloy containing, by weight, 15% or less of Co, 18-22% of Cr, 0.8-2.0% of Al, 5.0% or less of Ta, 0.5% or less of Mo, 0.5% or less of Ti, 13-18% of W, 0.05-0.13% of C, 0.06% or less of Zr, 0.015% or less of B, 0.4-1.2% of Mn, and 0.1-0.3% of Si, the balance of the alloy being preferably essentially made of Ni.

Abstract: A resinous shroud includes a resinous wall portion formed between a portion corresponding to a casing and a portion corresponding to a retaining member in a shroud portion when a resin material is filled from a gate portion. Thereby, a flow of the resin material to the portion corresponding to the casing from a portion corresponding to the gate portion can be dispersed by the resinous wall portion. Alternatively, an extended resinous wall portion may be formed in place of the resinous wall portion. Therefore, welds generated at the casing can be made small, and cambers generated at the casing can be suppressed.

Abstract: A compressor nozzle ring for an aircraft includes an inner shroud, an outer shroud and a multiplicity of blades extending from the inner shroud to the outer shroud. Each blade passes through the inner shroud and is attached to it with sealing cement containing an organic polymer adhesive. The adhesive is polyimide based.

Abstract: The present invention relates to a fan frame structure including a plastic frame and a metal fixing frame, in which at least two support arms are disposed on the rim of the fixing frame and extended outwardly therefrom, the outwardly extended distance of each support arm shall be beyond the range of an accommodation space of the frame, the portion of the support arm beyond the accommodation space in integrally enclosed by the plastic material of the frame. Therefore, the present invention not only significantly lowers the material cost, but also produces a variety of products in coordination with various specifications of fixing frame by using a single injection mold for the frame to save the mold cost.

Abstract: A turbine blade or vane for use in a gas turbine is to have as long a service life as possible at high strength. To this end, the turbine blade or vane, according to the invention, has a basic body which is formed from a strengthened cast ceramic material and in which a number of reinforcing elements are placed.

Abstract: There is described a method for coating the surfaces of turbomachines that come into contact with fluid media, wherein the outer surface of parts of turbomachines that come into contact with fluid media are contacted by a coating comprising an inorganic-organic hybrid polymer. Furthermore, there is described a turbomachine, wherein the surfaces that come into contact with fluid media have an outer coating which comprises an inorganic-organic hybrid polymer. Such a turbomachine can be used for generating electric power.

Abstract: A Ni-based alloy member has resistance against grain boundary fracture, fatigue strength, and oxidation resistance at temperatures near 1000° C. or higher. The Ni-based alloy member includes a non-repaired region made of a Ni-based alloy base and a region repaired by welding, which is formed on the non-repaired region and which is made of a buildup-welded layer, the buildup-welded layer being made of a Ni-based alloy containing, by weight, 15% or less of Co, 18-22% of Cr, 0.8-2.0% of Al, 5.0% or less of Ta, 0.5% or less of Mo, 0.5% or less of Ti, 13-18% of W, 0.05-0.13% of C, 0.06% or less of Zr, 0.015% or less of B, 0.4-1.2% of Mn, and 0.1-0.3% of Si, the balance of the alloy being preferably essentially made of Ni.

Abstract: A conformal seal (20) for sealing air flow between a cooling airflow path and a hot gas flow path within a combustion turbine engine. The conformal seal (20) may be fitted within cooperating side slots of adjacent vane segments (10) within the combustion turbine engine. The conformal seal (20) may include an elongated metallic substrate (22, 40) forming an upper surface and a lower surface. A conformal coating (26, 44) may be deposited over one or both surfaces of the substrate (22, 40). The conformal coating (26, 44) may be deposited to a depth so that a point contact between the conformal coating (26, 44) and respective interior walls of the side slots wears the conformal coating (26, 44) to establish surface area contact there between. The surface area contact improves a sealing function between the conformal coating (26, 44) and the respective interior walls during operation of the combustion turbine engine.

Abstract: A rotor for a rotating machine, in particular a steam turbine includes at least one subregion composed of a metal structure having a reduced density and including a multiplicity of finely distributed cavities.

Abstract: A compressor includes a compressor wheel, a diffuser and a device for the wet cleaning of the diffuser of a compressor, the diffuser being arranged downstream of the compressor wheel in the flow direction of the medium to be compressed. The device includes an arrangement for injecting a liquid, which is arranged in such a way that the liquid can be introduced, downstream of the compressor wheel, to the diffuser. The diffuser has at least partially a non-stick coating. A device of this type is suitable for removing deep-seated deposits from the surface of the diffuser.

Abstract: An assembly includes a first member and a second member, the first member including a first material composition and the second member including a second material composition. The first and second material compositions each include one or more isotopes of the same element, which are arranged to permit distinguishing between the first and second members or 0 parts thereof.

Abstract: Disclosed is an air intake for a turbocharger for an internal combustion engine, said air intake including a series of variable position guide vanes for directing the air such that it is swirling in a rotational sense on reaching the impeller of the compressor of the turbocharger. The variable position guide vanes are made comprised of sound absorbent material such as to achieve a substantial reduction in turbocharger noise at the air intake.

Abstract: Articles having substantially cylindrical bodies including a plurality of circumferential layers, each layer having at least one ply of material, the material comprising a weave fabric, a non-crimp fabric, or a combination thereof.

Abstract: A turbine engine fan casing for containing a separated blade fragment comprising a support case having an axially extending impact zone, a substantially structurally continuous penetrable covering circumscribing the impact zone; and a containment covering circumscribing the penetrable covering. The containment covering comprises a textile fabric containing threads in a warp direction and a fill direction, wherein the threads in the warp direction are of a different denier than the threads in the fill direction.

Abstract: The invention relates to a cooling fan for a cooling system of the internal combustion engine of a motor vehicle, the cooling fan comprising at least one frame (10) for retaining a fan motor and a fan motor (24) for driving a fan wheel (26). The invention is characterized in that at least one motor casing component of the fan motor (24) is injection-molded into the frame material and/or is coated by said material by injection molding when the frame (10) is formed. The invention also relates to a method for producing said cooling fan. The method according to the invention is characterized in that at least one motor casing of the fan motor (24) is injection-molded into the frame material and/or is coated by said material by injection molding when the frame (10) is formed.

Abstract: The invention relates to a component for arrangement in the duct of a turbine engine. The component is provided with a coating, which has a surface structure with scales which overlap each other in the direction of flow of the turbine engine. The invention also relates to a spraying method for generating a coating on a component.

Abstract: A protective ring (7) for a fan casing (2) of a gas-turbine engine equipped with a fan having especially metallic fan blades (3) includes a one-piece fiber-composite ring (8) with a ceramic cover (9) arranged on the ring inner surface facing the fan blades, and preferably formed by individual panels embedded in a ductile material, this cover (9)—upon the impingement of broken-off blade fragments—forms a crack network corresponding to an arrangement of the sintered starting ceramic particles and subsequently disintegrates into small particles, thereby absorbing a great part of the kinetic energy caused by the impinging blade fragment. Consequential damage to the protective ring is thereby minimized.

Abstract: A gas turbine ring segment (10) for use in gas turbine engines made from a ceramic matrix composite (CMC) material is disclosed. The ring segment includes a stacked multiplicity of CMC thin-sheet lamellae (25a, 25b) each comprising a peripheral surface collectively defining a cross-section profile of the ring segment. The lamellae collectively define a channel (11) formed in the center thereof for receiving a bow-tie member (27). The bow-tie member is disposed in the channel for holding together the stacked lamellae in a through thickness direction, and the in-plane strength of the bow-tie member is perpendicular to the in-plane strength of the lamellae. A stem portion (33) of the assembly may be further secured with a wrap (38) of CMC ribbon.

Abstract: A turbine component includes mounting structure for attaching the turbine component. A core is attached to the mounting structure. The core is made from a structural material. A plastic airfoil portion envelopes at least a portion of the core.

Abstract: Oilfield equipment is provided that includes a base material less subject to abrasion, corrosion, erosion and/or wet fatigue than conventional oilfield equipment materials such as carbon steel, and a reinforcing composite material for adding stress resistance and reduced weight to the oilfield equipment.

Abstract: A rotor (38) for a gas turbine engine (10) has a low emissivity surface finish, or high emissivity surface finish (44), on at least a portion of its surface (42) to reduce temperature differentials between an upper portion and a lower portion of the rotor (38). This reduces bowing of the rotor (38) to allow the gas turbine engine (10) to be started without harmful vibrations of the rotor (38).

Abstract: A gas turbine engine component includes a blade section having an inner end and an outer end, a shroud section at the outer end, and a platform at the inner end. A protective coating is disposed on the shroud, where the blade section is substantially free of the protective coating. The protective coating may also be disposed on the platform.

Abstract: A stator shell for a hydrodynamic torque converter (1), wherein said stator shell (2) comprises a plurality of blades (32, 34), wherein said stator shell (2) comprises plural components (20, 22), produced separately from one another and respectively comprising one or plural blades (32, 34) of said stator shell (2), wherein said components (20, 22) are fixated to one another and disposed relative to one another, so that blades (32, 34) of several of said components (20, 22) are disposed respectively offset relative to one another in a circumferential direction forming gaps provided in said circumferential direction extending about a central axis of the stator shell (2), wherein each of said blades (32, 34) is configured from an integral component between its respective leading edge and its respective trailing edge, so that each of the blades (32, 34) is respectively configured integrally from one of the components (20 or 22).

Abstract: The assembly comprises a stack structure made up of the following elements assembled together in pairs by brazing: the titanium-based metal piece (10); a first intermediate piece (11) suitable for deforming to accommodate differential expansion between the metal piece (10) and a piece (20) made of ceramic material based on silicon carbide and/or carbon; a second intermediate piece (12) that is rigid, having a coefficient of expansion close to that of said ceramic material piece (20) and made of aluminum nitride (AlN) or of tungsten (W); and the ceramic material piece (20).

Abstract: A method of manufacturing a gas turbine engine component includes the steps of forming a ceramic workpiece having oriented ceramic reinforcement, and severing the ceramic workpiece to produce a ceramic member having a desired orientation of the ceramic reinforcement. The ceramic member is then attached to a turbine engine component as a thermal barrier layer for the turbine engine component.

Abstract: An exemplary pump includes a pump housing defining a pump cavity, a movable pumping member situated in the pump cavity, and at least one pressure-absorbing member located inside the pump housing. The housing also has an inlet and an outlet, and includes at least one interior non-wearing location that contacts liquid in the pump housing when the pump housing is primed with the liquid. The movable pumping member, when driven to move, urges flow of the liquid from the inlet through the pump cavity to the outlet. The at least one pressure-absorbing member is located inside the pump housing at the non-wearing location and contacts the liquid. The pressure-absorbing member has a compliant property to exhibit a volumetric compression when subjected to a pressure increase in the liquid contacting the pressure-absorbing member, the volumetric compression being sufficient to alleviate at least a portion of the pressure increase.

Abstract: A composite gas turbine engine duct receives a support ring that operates as an interface arrangement for attachment of engine system components. The support ring interfaces with the composite duct through a fastener shear load arrangement to provide a structurally sound interface which minimizes the risk of ply delamination.

Abstract: A support apparatus for a gas turbine shroud is disclosed. The apparatus includes an outer shroud block having a coupling connectable to a casing of the gas turbine and a shroud component having a forward flange and an aft flange. The shroud component is attached to the outer shroud block via the forward flange and the aft flange. The apparatus further includes a damper disposed between the outer shroud block and the shroud component and a biasing element disposed within the outer shroud block. A translational degree of freedom between the damper and the outer shroud block defines a direction of motion of the damper. The biasing element is in operable connection between the outer shroud block and the shroud component via the damper, a bias force of the biasing element directed along the direction of motion of the damper.

Abstract: A plastic compressor housing, in particular a radial flow compressor housing, preferably for a turbocharger, has at least one thermosetting plastic body for providing an intake pipe, a compressor duct, and an outlet pipe, and a thermoplastic at least partially covering the thermosetting plastic body in a hood-like fashion. The thermosetting plastic body is formed as a basic body and the thermoplastic is injection molded on the basic body. At least a first anchoring element is embodied on at least a first surface of the thermosetting plastic body and at least a second surface of the first anchoring element is substantially completely covered with the thermoplastic. The disclosure further relates to a method for producing a plastic compressor housing.

Abstract: There are described components of a steam turbine, comprising a thermally insulating layer and a metallic anti-erosion layer on said thermally insulating layer. The anti-erosion layer is provided with the same material as the metallic connecting layer.

Abstract: A low leakage, integral fixed vane system for a gas turbine engine compression system which can accommodate the latest 3-D aerodynamic airfoil geometries and provide endwall ovalization control. A unitized construction wherein the vanes are integral with the case wall in the compression system.

Abstract: Flow energy installation with at least one in particular roller-like rotor (1) which rotates about an axis (A1) and has a plurality of rotor blades (2), wherein one, a plurality or all rotor blades (2) have associated with them at least one efficiency-improving air conducting fin (3) which in the direction of rotation is arranged upstream or downstream of the rotor blade (2) and/or the rotor is at least partly surrounded by at least one efficiency-improving diffuser element, and wherein the flow energy installation can be operated with liquid and/or gaseous media at any desired orientation of the axis (A1).

Abstract: A bearing bracket including a metal base and a bushing is provided. The metal base has an opening at its central portion. The bushing of the bearing bracket is made of plastic. The bushing encloses an axial portion or/and a radial portion of the metal base by injection molding. Furthermore, the bearing bracket further includes an anti-vibration member disposed on at least one side surface of the metal base.

Abstract: A method for manufacturing a torque converter includes providing an outer race of a one way clutch, contacting the outer race with a side plate, and casting a stator housing together with the outer race and the side plate. A torque converter is also provided.

Abstract: The aim of the invention is to provide a superheated component of a steam turbine installation with high thermal and mechanical resistance. To this end, the component comprises a lining applied to a body of the component, on a hot side facing a steam chamber, said lining being adapted to the contour of the component body. According to the invention, the lining comprises a number of moulded parts, each moulded part comprising a metallic and ceramic composite layer formed from at least one metallic layer and at least one ceramic layer. The ceramic layer is used especially as a insulating layer, and the metallic layer is especially used as a support or for protection against abrasion and/or erosion.

Abstract: Blades for gas turbine engines which are formed from composite materials have problems with respect of resistance to impacts such as bird strikes. Previous blades formed from metals had some ductility towards the trailing edge which could accommodate the whiplash effects of impacts. With regard to composite materials such ductility is not present. By providing projections 32 which act as propagation wave trips as well as high intensity reflectors 36 it is possible to limit the whiplash at the edge 31 resulting in damage. Typically a cladding cap 38 is provided which also may be formed from a metal to allow some greater uniformity with respect to mass per length despite the tapering of the blade. Furthermore by providing voids which act as delamination initiation sites cracking can be provided between plies which allows greater flexibility towards the edge and therefore release of energy. These voids may incorporate uncured polymer matrix to act as a binder subsequent to delamination.

Abstract: A steam turbine power plant which is provided with an extra-high-pressure turbine 100, a high-pressure turbine 200, an intermediate-pressure turbine 300 and a low-pressure turbine 400, and has high-temperature steam of 650° C. or more introduced into the extra-high-pressure turbine 100, wherein the extra-high-pressure turbine 100 has an outer casing cooling unit which cools an outer casing 111, and a turbine rotor 112, an inner casing 110 and a nozzle box 115 of the extra-high-pressure turbine 100 are formed of an Ni base heat-resisting alloy, and the outer casing 111 is formed of a ferrite-based alloy.

Abstract: A turbine vane includes a platform; and at least one airfoil mounted to the platform and having a trailing edge and a leading edge, wherein the vane is composed of a functionally graded material having a first material and a second material, wherein the trailing edge includes a greater amount of the first material than the second material, and the leading edge includes a greater amount of the second material than the first material.

Abstract: A burn resistant composite article includes at least one composite layer having first fibers within a first organic resin matrix. At least one burn resistance layer is disposed adjacent the at least one composite layer. The burn resistance layer includes second fibers within a second organic resin matrix. The composite layer and the burn resistance layer each have an associated thermal resistance, and the thermal resistance of the burn resistance layer is greater than the thermal resistance of the composite layer.

Abstract: A turbocharger includes a compressor housing and a turbine housing wherein at least one of the compressor housing and the turbine housing includes an anti-ballistic material such as, for example, aramid fibers, S glass fibers and/or carbon fibers. A turbocharger system optionally includes a temperature controller that controls temperature in instances where operational temperatures may be detrimental to the performance characteristics of anti-ballistic material. Various other exemplary devices, methods, systems, etc., are also disclosed.

Abstract: A mounting apparatus for a fan (30) includes a chassis (10), and a locking member (40). The chassis includes a bottom plate (12), two parallel installing plates (22, 24) perpendicularly secured on the bottom plate, and two parallel partition plates (26) perpendicularly secured between the installing plates. The partition plates are perpendicular to the bottom plate. One of the plates defines a cutout (264) offset from a middle of an edge thereof. The locking member engages with the one plate for securing the fan between the plates. A positioning block (424) is formed on the locking member, and engages in the cutout of the one plate for inserting the fan between the plates along a predetermined direction.

Abstract: Embodiments of the invention relate to a vane assembly formed by a forward airfoil segment and an aft airfoil segment. The aft segment is made of metal and can define the trailing edge of the vane assembly. The forward segment can be made of ceramic, CMC or metal. The forward and aft segments cannot be directly joined to each other because of differences in their rates of thermal expansion and contraction. The forward and aft segments can be positioned substantially proximate to each other so as to form a gap therebetween. In one embodiment, the gap can be substantially sealed by providing a coupling insert or leaf springs in the gap. A separate metal aft segment can take advantage of the beneficial thermal properties of the metal to improve cooling efficiency at the trailing edge without limiting the rest of the vane to being made out of metal.

Abstract: A vane has an airfoil shell and a spar within the shell. The vane has an outboard shroud at an outboard end of the shell and an inboard platform at an inboard end of the shell. The shell includes a region having a depth-wise coefficient of thermal expansion and a second coefficient of thermal expansion transverse thereto, the depth-wise coefficient of thermal expansion being greater than the second coefficient of thermal expansion.

Abstract: The invention relates to a turbo machine comprising a housing. Said turbo machine is designed especially as a turbo compressor for use at low temperatures, the housing preferably being made of a cold-resistant material that has a martensitic structure.

Abstract: A compressor blade (30) comprises a vibration damping coating (54) on a first surface of at least one portion of an erosion resistant material (56). The vibration damping coating (54) comprises a plurality of segments (58). The portion of erosion resistant material (56) and the vibration damping coating (54) are adhesively bonded to the compressor blade (30) such that the vibration damping coating (54) is arranged between the surface (50) of the compressor blade (30) and the portion of erosion resistant material (56).

Abstract: A nacelle assembly includes an inlet lip section and a cowl section downstream of the inlet lip section. At least a portion of the cowl section is flexed to take various shapes through a nanoelectromechanical system and thereby influence an effective boundary layer thickness of the nacelle assembly.

Abstract: A plastic compressor housing, in particular a radial compressor housing, preferably for a turbocharger, includes at least one first housing part and at least one second housing part, which respectively comprise at least in some areas at least one thermoset material. The first housing part and/or the second housing part comprises or comprise at least two individual elements, wherein the first housing part and the second housing part are coated at least in some areas with at least one thermoset body or at least one thermoplastic body such that the first housing part, the second housing part and the individual elements of the first housing part and/or the second housing part respectively are in contact at least in some areas with the thermoset body or the thermoplastic body. Also disclosed is a method for producing a plastic compressor housing and a turbocharger.

Abstract: A method for manufacturing a multi-resin composite article is provided. The method comprises providing at least one fiber preform in a mold; injecting a plurality of resins into the at least one fiber preform at a plurality of locations on the at least one fiber preform; and forming at least one transition region along a mutual contact surface between the resins. Each of the at least one transition regions is defined by a gradual transition in composition from one of the resins to another of the resins. A multi-resin composite article is also provided. The article comprises: at least one fiber preform; a plurality of resins, wherein the at least one fiber preform is infused with the resins; and at least one transition region extending along a mutual contact surface between respective ones of the resins. A system for manufacturing such a multi-resin composite article is also provided.