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 coefficient of thermal expansion (CTE) varying with depth.

Abstract: A super steam turbine (100) into which high-temperature steam of 650° C. or more is introduced is provided with an inner steam pipe (120) which is disposed through an inner casing (110) and an outer casing (111), an outer steam pipe (130) which is welded to the outer casing (111) and disposed outside of the inner steam pipe (120) along the inner steam pipe (120) with a prescribed space therebetween, and a radiation heat shielding pipe (140) which is disposed along the inner steam pipe (120) between the inner steam pipe (120) and the outer steam pipe (130) to face a welded portion of at least the outer steam pipe (130), wherein cooling steam (160) is flown between the inner steam pipe (120) and the outer steam pipe (130), respective component parts are made of a suitable heat-resisting steel having prescribed chemical composition ranges.

Abstract: An article for protecting an airfoil component includes a sheath having an outer side and an inner side that forms a cavity for receiving a leading edge of the airfoil component. The sheath is made of cobalt and phosphorous to protect the leading edge of the airfoil component from erosion.

Abstract: The restoring process machines out a crack in the platform of a turbine blade to form a pocket that then receives a plug of compatible material. The plug is brazed in place and the blade is the machined and cleaned to present a clean fresh surface where the plug is inserted. The plug has a lower coefficient of thermal expansion so that the plug area has less compressive stresses in the repaired area.

Abstract: A gas turbine stator includes a vane assembly, and a platform that is configured to receive the vane assembly. The vane assembly includes a vane and a cap. The vane extends radially from the cap. The vane includes a pressure side shell and a separate suction side shell.

Abstract: An exemplary vane fronting surface for a variable geometry turbine includes a white layer that comprises nitrides. Such a layer may be formed using gas nitriding. As described, trials demonstrate that such nitriding reduces friction between a vane fronting surface and vanes of a variable geometry turbine. Consequently, nitriding can enhance longevity and controllability of a variable geometry turbine.

Abstract: A multistage pump according to the present invention has a plurality of intermediate casings (2) formed by press-forming a steel plate. The intermediate casing has a cylindrical side portion (21), a stage flat portion (23) with which an axial end face of an adjacent intermediate casing is held in contact, a stage side portion (24) extending axially from the stage flat portion, and a bottom portion (25) extending radially inward from the stage side portion. A relief plate (30) having an outer circumferential end face which is held in contact with an inner surface of a cylindrical side portion of the adjacent intermediate casing is attached to the bottom portion of the intermediate casing. The relief plate, the stage side portion, the stage flat portion, and the inner surface of the cylindrical side portion of the adjacent intermediate casing form a space in which an O-ring (40) is fitted.

Abstract: A pump assembly has a housing formed of at least two metallic housing parts (2) and at least one diffuser (12) arranged in the housing, wherein the diffuser (12) is fixed between the two housing parts in the axial direction, and the two housing parts (2) are directly or indirectly in metallic contact with one another, in a manner such that a force transmission in the axial direction between the housing parts (2) is effected via elements of metal.

Abstract: A flow-guiding member unit used for assembling a flow-guiding member comprising pluralities of vanes, an outer platform and an inner platform, the unit comprising an integral body member comprising one vane portion, an outer platform portion, and an inner platform portion, a first elastic member attached to a step of the outer platform portion, and a second elastic member attached to a step of the inner platform portion, the body member being formed by the thermal compression of sheet-molding compounds or fiber-reinforced resin pellets, and the first and second elastic members being made of a thermoplastic elastomer.

Abstract: According to the invention, the air intake (2) is made of a piece (23) of fibre/resin composite material, reinforced on the side of the flange (24) by a reinforcing ring (26).

Abstract: A CMC wall (22) with a front surface (21) heated (24) by a working fluid in a gas turbine. A back CMC surface (23) is coated with a layer (42) of a thermally conductive material to accelerate heat transfer in the plane of the CMC wall (22), reducing thermal gradients (32-40) on the back CMC surface (23) caused by cold spots (32) resulting from impingement cooling flows (26). The conductive material (42) may have a coefficient of thermal conductivity at least 10 times greater than that of the CMC material (22), to provide a minimal thickness conductive layer (42). This reduces thermal gradient stresses within the CMC material (22), and minimizes differential thermal expansion stresses between the CMC material (22) and the thin conductive layer (42).

Abstract: A turbofan gas turbine engine (10) comprises a fan rotor (32) carrying a plurality of radially extending fan blades (34). A fan blade containment assembly (38) surrounds the fan blades (34) and the fan blade containment assembly (38) comprises a generally cylindrical, or frustoconical, metal casing (40). The casing (40) comprises an annular member (54) positioned axially upstream of the tip (37) of the fan blade (34). The annular member (54) extends in a radially inwardly and axially downstream direction from the metal casing (40) towards the tip (37) of the fan blade (34). A set of cassettes (120) carries fan blade track panels (71B,71C,71D). The cassettes (120) are secured to the metal casing (40) by axially extending members (124,128) on the upstream and downstream ends (122,126) of the cassettes (120) which locate on the annular member (54) and are secured to inserts (136) on the inner face of the casing (40).

Abstract: An object is to provide a method for forming a superior corrosion-resistant plating layer by sealing penetrating pinholes formed in an electroless plating layer. There are provided a first plating step of performing electroless Ni—P plating on a base material (1); an etching step of etching a surface of a first plating layer (3) formed by the first plating step; and a second plating step of performing electroless Ni—P plating to form a second plating layer (5) on the first plating layer (3) processed by the etching step.

Abstract: A gas turbine having at least one compressor, at least one combustion chamber, and at least one turbine, the or each compressor and/or the or each turbine having a rotor that includes rotor blades surrounded by a stationary housing, and a run-in coating being assigned to the housing is disclosed. The gas turbine includes at least one channel which is configured to apply a pressure prevailing on the high-pressure side of the blades of a rotor to a low-pressure side of the same in the area of a gap between the radially outer ends of the blades and the housing and thereby prevent a flow through the gap.

Abstract: The article comprises a substrate having a first surface, a plurality of elements extending from the first surface, and a protective coating disposed between at least a portion of the plurality of elements, on at least a portion of the plurality of elements, or both. The plurality of elements are integral with the substrate. A method for applying a protective coating onto an article is also provided.

Abstract: The invention relates to a guide-vane arrangement (1) for deviating the flow present in the by-pass flow channel (2) of an engine (3), said arrangement comprising an outer ring (4) and an inner ring (5) and guide vanes (6) arranged therebetween in a substantially radial manner, wherein the outer ring (4) has elements (7) for connecting to an outer engine structure (8), and the inner ring (5) has elements (9) for connecting to an inner engine structure (10), with a plurality of segments (11) being provided.

Abstract: A pipe for a steam turbine is formed of a centrifugal casting material to achieve resistance against higher temperatures and improve reliability of the pipe by employing, as a pipe material, a centrifugal casting material normalized to contain uniform and finer crystal grains. The centrifugal casting material is made of steel having a columnar structure in the radial direction with the crystal grain size number of 5 or more in a plane perpendicular to the radial direction. The steel includes 0.05-0.5% by mass C, not more than 1.0% Si, 0.05-1.5% Mn, 0.01-2.5% Ni, 8.0-13.0% Cr, 0.05-2.5% Mo, not more than 3.0% W, 0.05-0.35% V, 0.01-0.5% Nb, not more than 5% Co, 0.01-0.1% N, not more than 0.03% B, and not more than 0.05% Al.

Abstract: A centrifugal pump includes a diffuser section for decreasing a velocity of the fluid discharged from an impeller, a return vane for leading the fluid which has passed through the diffuser section to a discharge side, and a main plate to which the diffuser section and the return vane are fixed.

Abstract: Apparatus including a locomotive-radiator-cooling-fan tankhead assembly having a substantially-circular base plate and a substantially-circular outer ring. The base plate has a central longitudinal axis and a circumference. The outer ring is substantially coaxially aligned with the central longitudinal axis and is attached to the base plate proximate the circumference. The base plate has a substantially-planar first surface having a central recess substantially coaxially aligned with the central longitudinal axis and having circumferentially-separated, first and second peripheral recesses each radially spaced apart from the central recess and extending radially inward from proximate the circumference. The outer ring longitudinally extends beyond the first surface. The tankhead assembly is devoid of any gussets attached to the base plate and is devoid of any gussets attached to the outer ring.

Abstract: A turbocharger includes a center housing having a bearing surface configured to contact an inner surface of a unison ring. A conversion coating is impregnated onto at least the bearing surface of the center housing.

Abstract: An impeller including a plurality of longitudinally-extending blades, each having a first edge and a second edge, a cover member with an inlet orifice and extending along at least a portion of the first edge of each of the plurality of blades, and a hub member extending adjacently along only a portion of the second edge of each of the blades. The cover member, plurality of blades and hub member are milled from a single, metal-based material of construction to form an integral, uniform structure. A kit for an impeller assembly and a method of manufacturing an impeller are also disclosed.

Abstract: A method provides fire protection for titanium components of an aircraft gas turbine. To enable the use of titanium components on aircraft gas turbines without the risk of titanium fire, a surface-near, nonflammable, intermetallic phase of titanium and at least one further metal, selected from the group of aluminum, nickel, vanadium and chromium, including combinations thereof, is produced in the surface of the component by a diffusion process.

Abstract: The present invention provides a compressor housing capable of reducing the weight of a compressor without leading to an increase in the size and a reduction in the efficiency of the compressor. The compressor housing includes: an inner cylinder made of a plastic material and extending in an axial direction and in a circumferential direction to surround blade tips of the blades; and an outer cylinder made of a plastic material and extending in the axial direction and in the circumferential direction to surround the inner cylinder. The inner cylinder and the outer cylinder are bonded or jointed at the first end, opposite the second end where the volute is formed.

Abstract: According to the invention, the internal wall (5.1) of the air intake (2) and the housing (12.1) for the fan (3) are pieces of composite fibre/resin material, overlap-jointed at the ends thereof (5.1R) and (12.1A).

Abstract: The invention relates to the use of a thermal insulating layer for a housing of a steam turbine in order to even out the deformation behavior of different components based on different heatings of the components.

Abstract: A replacement fan exit guide vane assembly for installation between an inner case and an outer case of a gas turbine engine includes an airfoil structure having an outer end and an inner end, a wedge structure connected to the outer end of the airfoil structure, a base plate positioned between the outer end of the airfoil structure and the outer case, a conformable material, and a slip collar having an opening therethrough and a recess formed along the opening. The airfoil structure extends through the opening, and the recess accepts the wedge structure to create an interference fit between the slip collar and the base plate. The conformable material is disposed along the opening and the recess in the slip collar, and also along the baseplate, in order to provide dampening relative to the airfoil structure and the wedge structure.

Abstract: A gas turbine engine airfoil is made from separate cast sections having different cast alloy structures. The cast alloy structures are selected on the basis of the local operating conditions of each section. Friction welding can be used to join the sections together.

Abstract: A rear fan case for a gas turbine engine includes a main body and a discrete joining arrangement mounted on the outside of the main body towards its rear end. The joining arrangement provides a substantially radial groove around the main body, which can receive a joining blade on a thrust reverser unit to form a joint between the rear fan case and the thrust reverser unit. The joining arrangement may be made of metal while the main body is made of composite material. Features may be provided to ensure proper alignment and location of the joining arrangement.

Abstract: Turbine components with different types of coatings on different parts thereof are described. The coatings are chosen such that they are especially adapted to the thermal and corrosive conditions being present on the parts of the component during use. A method to coat a turbine component is also described.

Abstract: A ring structure with a metal design for a moving blade of axially flowed through compressor and turbine stages, particularly in gas turbine engines is provided. The ring structure includes a circular ring-shaped outer wall, a circular ring-shaped inner wall, which is located at a short radial distance from the moving blade tips, and includes a joining structure provided in the form of hollow chamber structure between the outer wall and the inner wall. The outer wall is provided in the form of a closed, mechanically stable housing wall of the compressor or turbine stage, and the joining structure provided in the form of hollow chamber structure is joined in a fixed manner to the outer wall and to the inner wall, for example, by soldering, diffusion welding or other joining techniques. The inner wall is provided in the form of a closed, mechanically stable structure, which serves as a run-in lining for the moving blade tips and which is made of a metal woven fabric and/or of a metal felt.

Abstract: This hydraulic machine member has at least one flow of water passing through it, and comprises at least one wetted surface extending between two edges of the member, at least one of the edges of the member and part of the adjacent wetted surface being reinforced and formed by at least one removable solid element made from material having a high resistance to abrasion.

Abstract: An Ni-base alloy for a turbine rotor of a steam turbine contains in percent by weight C: 0.05 to 0.15, Cr: 22 to 28, Co: 10 to 22, Mo: 8 to 12, Al: 0.8 to less than 1.5, Ti: 0.1 to 0.6, B: 0.001 to 0.006, Re: 0.1 to 2.5, and the balance of Ni and unavoidable impurities.

Abstract: The ‘hydrokinetic turbine assembly’ is a device for the conversion of the kinetic energy of oscillating tidal currents into rotary torque to generate clean electric power. This device is a horizontal axis hydroturbine with a plurality of trapezoidal symmetrical blades placed at about 45 degrees to the axis. The inclination of the blades assures its maximum energy conversion capacity and the dual reaction function of the turbine where ‘floods and ebbs” are alternatively converted into rotary torque. The inner blade frame, its aerodynamic contour, and at least one connective circumferential blade-ring, add strength buoyancy and sensitivity to slow currents. This hydrokinetic turbine is separated from the electric generators and can be placed in pre-planned current flow locations for greater efficiency.

Abstract: A ceramic matrix composite nozzle assembly. The ceramic matrix composite nozzle assembly may include a ceramic matrix composite vane, a number of metallic components positioned about the ceramic matrix composite vane, and a number of metallic seals positioned between the ceramic matrix composite vane and one or more of the metallic components.

Abstract: Thermal barrier coating layer systems, in addition to good thermal barrier properties, also have to have a long service life of the thermal barrier coating. The layer system according to the invention comprises a specially adapted layer sequence of metallic bonding layer, inner ceramic layer and outer ceramic layer.

Abstract: An airfoil or vane for a combustive power plant includes an inner core formed from a first composite material having discontinuous fibers. An outer sleeve is formed from a second composite material having continuous fibers. The first composite material is different from the second composite material. The outer sleeve generally surrounds and is bonded or otherwise connected to the inner core. A method of fabrication includes injecting or otherwise introducing thermoplastic fiber composite material including chopped or otherwise discontinuous fibers into a mold to form the core and platforms of an airfoil assembly. The injected thermoplastic fiber composite material is then cured in the mold. The cured thermoplastic fiber composite material is then removed from the mold. A layup including one or more surface plies of a thermoset continuous fiber composite material is then applied to the core material. The surface plies are then compressed and cured in a mold.

Abstract: A damaged gas turbine blade which has previously been in service, and which is made of a base metal, is furnished. Any damaged material is removed from the damaged blade tip. The damaged blade tip is weld repaired with a nickel-base superalloy that is more resistant to oxidation resistance than is the base metal in the operating environment of the tip-repaired gas turbine blade. The method does not include any step of coating a lateral surface of the repaired blade tip with a non-ceramic coating after the step of weld repairing.

Abstract: A containment case comprises a composite core, with an inner surface, and at least one ceramic layer integrated with the composite core. The at least one ceramic layer is bonded to the inner surface of the composite core with a resin. In another embodiment, a containment case comprises a composite core, with an inner surface, and a hybrid material comprising at least one ceramic material and at least one non-ceramic material. The hybrid material is disposed on the inner surface of the composite core. The hybrid material is bonded to the inner surface of the composite core with a resin. A method of fabricating a containment case includes the steps of disposing one or more layers of ceramic fabric on an inner surface of a composite core, infusing the composite core and the one or more layers of ceramic fabric with resin, and curing the resin.

Abstract: A method for forming a dense coating on a limited region of a subject body is disclosed. The method is composed of the steps of: applying one selected from the group of a compressed body of a powder of a metal and a sintered compressed body of a powder of a metal to a working electrode; executing discharge deposition to deposit a first coating from the working electrode on the subject body by applying the subject body as a workpiece of the discharge deposition; executing discharge deposition to deposit a second coating from the working electrode on the first coating by applying the subject body as a workpiece of the discharge deposition; and heating the subject body in one selected from the group of a vacuum, an air and an oxidizing atmosphere so as to densify the second coating or oxidizing the second coating at least in part to generate a solid lubricant substance.

Abstract: The invention relates to a turbomachine part comprising a main portion and a leading edge. Over at least a fraction of the length of said part, the leading edge is constituted by a sheet of material that is fastened to the main portion and that extends from the pressure side to the suction side of the main portion while leaving a space between the sheet and the upstream end of the main portion, said material being capable, below a maximum deformation ?2, of responding to an impact against a foreign body by deforming reversibly in superelastic manner without damaging the main portion.

Abstract: A vacuum pump is provided in which gas molecules in a vacuum chamber are sucked and exhausted by the rotational motion of a rotor rotatably supported in a pump case. At least one nickel alloy layer is disposed on a surface of at least one component defining a flow path in the vacuum pump for increasing a resistance of the component to corrosion due to a corrosive effect of a gas flowing through the flowpath. A nickel oxide is formed on a surface of the nickel alloy layer and has a higher emissivity than that of the nickel alloy layer for increasing a quantity of heat radiated from the surface of the component when the component is heated during operation of the vacuum pump.

Abstract: A nickel-base superalloy having excellent oxidation resistance is provided. It is useful as high-temperature members such as turbine blades and turbine vanes for jet engines or gas turbines. The nickel-base superalloy has a composition containing Co: 0.1 to 15% by weight, Cr: 0.1 to 10% by weight, Mo: 0.1 to 4.5% by weight, W: 0.1 to 15% by weight, Al: 2 to 8% by weight, Ta+Nb+Ti: 0 to 16% by weight, Hf: 0 to 5% by weight, Re: 0.1 to 16% by weight, Ru: 0.1 to 16% by weight, Si: 0.2 to 5% by weight and a balance made of Ni and unavoidable impurities.

Abstract: A nozzle assembly for directing cooling fluid in a vane comprising a hollow airfoil containing at least two cooling chambers. The chambers are separated by a generally radial rib. A metering plate mount is attached to the rib. A metering plate, having at least one aperture for tuning the cooling fluid flow within the airfoil, is adjacent the metering plate mount.

Abstract: An enhanced environmental barrier coating for a silicon containing substrate. The enhanced barrier coating may include a bond coat doped with at least one of an alkali metal oxide and an alkali earth metal oxide. The enhanced barrier coating may include a composite mullite bond coat including BSAS and another distinct second phase oxide applied over said surface.

Abstract: A novel method of manufacturing a turbine frame for rotatably holding adjustable blades in a VGS turbocharger is provided, which method is capable of manufacturing the turbine frame while almost eliminating a time-consuming cutting operation, whereby mass production of the turbine frame and the like can be realized. The method includes: a blank which is punched out from a metal material having a substantially constant thickness in such a manner as to integrally include a boss forming portion (24a) and a flange forming portion (23a) is used as a shaped material (W) serving as an original member for the turbine frame; when the shaped material (W) is processed, the boss forming portion (24a) is formed into a projecting state by a press forging tool; receiving holes for rotatably holding the respective adjustable blades are formed in the flange forming portion (23a) by punching; and when the shaped material (W) is processed, some or all of the manufacturing processes are carried out in a warm condition.

Abstract: This invention is directed to nacelles and nacelle components for use in aircraft engines. The nacelles and components comprise composite material containing carbon fiber. The carbon fiber comprises from 0.1 to 20 percent by weight nanoreinforcement material.

Abstract: The present invention relates to a stator (100-1000) with a profiled helical bore (106,206,306,606,706,806,906,1006) having a cast material layer (102;202;302;602;702;802;902;1002) with transducers (104A-104D;304;604A-604D;710;804;904A-904C;1010) disposed therein and describes the methods of forming such stators. Cast material can be fluidic during displacing of a transducer therein. Cast material layer 202 can include housings (218,222) disposed therein and/or a cavity 226 formed therein. Transducer can be a sensor (104A-104C) and/or an actuator 104D. Transducer 804 can extend axially along a length of the stator 800. Transducer or plurality of transducers (904A-904C) can extend along a helical path. Additionally or alternatively, sleeve 1008 can include a transducer 1010.

Abstract: A method for producing a wear-resistant, temperature-resistant, and corrosion-resistant protective coating for a component, in particular for components of a gas turbine, using thermal spraying, wherein during the application onto the component of the protective coating, which consists of a hard material-metal combination, in order to produce an abrasive surface a structuring of that surface of the protective coating that faces away from the component takes place, the hard material or materials consisting of boron nitride particles, titanium carbide particles, tungsten carbide particles, chromium carbide particles, and zirconium oxide particles, or a mixture thereof, and the hard materials having a particle size of 0.1 ?m-200 ?m, and the protective coating having a thickness of 10 ?m-6.0 mm.

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: A stator vane assembly for a compressor has a support structure which carries and is bounded by an annular stator vane structure. The stator vane structure comprises a central bore and a sleeve carried on the central bore. The sleeve is disposed between the support structure and bore of the annular stator vane structure. The annular stator vane structure is made from a non-metallic composite material and the sleeve is made from a first material. The coefficient of thermal expansion of the non metallic material is equal to or less than the co-efficient of thermal expansion of the first material.