Abstract: To provide a stator member that facilitates thermal radiation from a surface thereof and thermal conduction to an adjacent member, and a vacuum pump that contains the stator member. For the purpose of enhancing heat dissipation of a rotor portion, surface treatment removal processing is performed on a predetermined section of a thread groove spacer in order to efficiently release heat of the thread groove spacer toward a base and a stator blade spacer. More specifically, the surface treatment removal processing removes the surface treatment of the base and a section where the stator blade spacer comes into contact with the thread groove spacer. This surface treatment removal processing is executed simultaneously with finishing processing.

Abstract: An assembly that includes an impeller having an upper face, a lower face, and a central bore sized and shaped to mate with a connecting end of a shaft. The central bore is defined by a plurality of ledges that each include a cement groove, and channels disposed between the ledges. The connecting end includes a plurality of slots, and extended grooves disposed between the slots. Each extended groove includes an end that extends perpendicular to the length of the extended groove. In application, the plurality of ledges frictionally communicate with the outer surface of the shaft. The plurality of channels of the impeller align with the plurality of grooves of the shaft defining passages that provide a tunnel for entrainment of particles entering the impeller. The cement grooves of the impeller further align with and receive the extended grooves and ends of the shaft resulting in a stronger connection between the shaft and impeller.

Abstract: A method of manufacturing an article comprises providing a ring for an etch reactor. Ion assisted deposition (IAD) is then performed to deposit a protective layer on at least one surface of the ring, wherein the protective layer is a plasma resistant rare earth oxide film having a thickness of less than 300 ?m and an average surface roughness of less than 6 micro-inches.

Abstract: A machine component including a base body produced from a base material is provided. The base body is equipped in a partial region of the surface thereof with a plating made of an application material having a greater hardness and/or viscosity as compared to the base material. The plating is foamed by a number of plating elements that are applied to the base body in the longitudinal direction thereof in a tilted manner relative to the main flow direction of a hot gas flowing through the base body.

Abstract: Disclosed is a coating for protecting a component against high temperatures and aggressive media, which coating has at least one subregion whose main constituent is chromium. The layer additionally comprises aluminum, the chromium content at least in the subregion in which chromium is the main constituent being greater than 30% by weight and the aluminum content being greater than or equal to 5% by weight. The invention further provides a process for producing such a coating, comprising chromizing the surface to be coated and subsequently alitizing the chromium-rich layer produced during chromizing.

Abstract: A method of manufacturing a fan case with a liner includes the steps of providing a preform having a circular cross-section with a cut and a first diameter, flexing the preform to reduce the first diameter to a second diameter, and adhering the preform to an inner surface of a fan case. A fan case for a gas turbine engine includes a fan case body having an inner surface. A preform is adhered to the inner surface and has a cut providing a gap.

Abstract: The invention relates to an angular sector of a bladed stator of a low-pressure compressor of an axial turbine engine. The sector comprises an outer shroud and an inner shroud in the form of circular arcs intended to be mounted in a concentric manner on the outer casing of the turbine engine compressor. The sector likewise comprises a row of stator vanes extending radially and anchored in the shrouds in such a manner as to form a bladed box. The vanes of the box comprise anchoring lugs at their outer ends, the lugs being disposed in the thickness of the outer shroud. The inner shroud comprises stubs for anchoring vanes.

Abstract: There is provided a method for manufacturing a turbocharger bearing housing which can prevent a collapsible core from being damaged when molten metal is cast in the mold. The method for manufacturing a bearing housing of a turbocharger is that the bearing housing of the turbocharger is formed with a cooling passage for circulating cooling liquid by casting using a collapsible core. The collapsible core includes the end part forming portions (a one end forming portion and an other end forming portion) corresponding to the end portions of the cooling passage and having a substantially elliptical cross-section, and a fixing portion holding the end part forming portions and being embedded in a mold and fixed to the mold.

Abstract: In some examples, a coating may include at least one feature that facilitates visual determination of a thickness of the coating. For example, the coating may include a plurality of microspheres disposed at a predetermined depth of the coating. The plurality of microspheres may define a distinct visual characteristic. By inspecting the coating and viewing at least one of the microspheres, the thickness of the coating may be estimated. In some examples, the plurality of microspheres may be embedded in a matrix material, and the distinct visual characteristic of the microspheres may be different than the visual characteristic of the matrix material. In other examples, the at least one feature may include at least one distinct layer in the coating system that includes a distinct visual characteristic, such as a color of the distinct layer.

Abstract: A process for producing a welded joint, which includes a weld metal having high strength and high toughness, and containing fewer blowholes, includes the steps of: preparing a base material containing, by mass %, not less than 10.5% of Cr; and subjecting the base material to GMA welding using a shielding gas containing 1 to 2 volume % or 35 to 50 volume % of CO2 gas, and the balance being inert gas, thereby forming a weld metal includes, by mass %, C: not more than 0.080%, Si: 0.20 to 1.00%, Mn: not more than 8.00%, P: not more than 0.040%, S: not more than 0.0100%, Cu: not more than 2.0%, Cr: 20.0 to 30.0%, Ni: 7.00 to 12.00%, N: 0.100 to 0.350%, O: 0.02 to 0.11%, sol. Al: not more than 0.040%, at least one of Mo: 1.00 to 4.00% and W: 1.00 to 4.00%, and the balance being Fe and impurities.

Abstract: A segmented shroud ring surrounds a circumferential array of blades of a gas turbine engine rotor. The shroud ring has a plurality of shroud segments disposed circumferentially one adjacent to another. The circumferentially adjacent shroud segments have confronting sides defining an inter-segment gap therebetween. The inter-segment gaps are sealed by a sealing band mounted to the radially outer surface of the segmented shroud ring so as to extend across the inter-segment gaps around the full circumference of the shroud ring. Impingement jet holes may be defined in the sealing band for cooling the shroud segments.

Abstract: An impeller is comprised of a hub configured to be rotated on a central axis, a shroud formed to be opposed to the hub in a direction of the central axis and having a central opening serving as a fluid inlet, and a plurality of circumferentially-equidistant spaced blades interleaved between the hub and the shroud. When a mating face of the shroud with each of the blades is divided into a radially inward region and a radially outward region, and a mating face of each of the blades with the shroud is divided into a radially inward region and a radially outward region, a given weld range is set only in the radially inward region of the mating face of the shroud with each of the blades and the radially inward region of the mating face of each of the blades with the shroud.

Abstract: An impeller assembly including a housing and an impeller is provided. The impeller is positioned within a volute of the housing and includes a hub and a plurality of blades. The plurality of blades are spaced about the hub along a circumferential direction of the impeller. The plurality of blades include a first pair of blades and a second pair blades. The first pair blades defines a first gap along the circumferential direction at a radially outer portion, and the second pair blades defines a second gap along the circumferential direction at a radially outer portion. The first gap is unequal to the second gap in order to reduce an amount of noise generated by the impeller assembly.

Abstract: In accordance with an exemplary embodiment, a method for manufacturing a component using additive manufacturing techniques includes providing a 3D design model for the component, adding one or more crack resistant features to the 3D design model of the component to produce an enhanced design model, and manufacturing the component using an additive manufacturing technique in accordance with the enhanced design model. The one or more crack resistant features are provided to reduce or eliminate the incidence of cracking in the manufactured component.

Abstract: A method of manufacturing graphene includes preparing a support member, disposing a carbon layer on the support member, disposing a catalyst layer on the carbon layer, forming graphene on the catalyst layer, attaching a carrier to the graphene and forming a graphene-forming structure, separating the support member from the graphene-forming structure, and removing the catalyst layer.

Abstract: A casing for an aircraft engine includes an outer ring and an inner hub defining an airflow passage therebetween, the outer ring having an axis defining an axial direction; a plurality of struts arranged in a circumferential array and extending radially from the inner hub to the outer ring to mount the inner hub to the outer ring; wherein the outer ring is defined by a double skin including an axially-extending annular outer skin of sheet metal concentrically surrounding and radially-spaced from an annular inner skin of sheet metal, the outer and inner skins generally parallel to one another, an annular front end ring and an annular rear end ring welded or brazed to the outer and inner skins adjacent respective front and rear edges of the skins to define an annular cavity between them, and the outer ring further comprising a plurality of circumferentially spaced axially-extending ribs interconnecting the outer and inner skins to reinforce the double skins.

Abstract: A flow sleeve assembly for a combustor of a gas turbine includes an annular support sleeve disposed at a forward end of the flow sleeve assembly. The support sleeve includes a forward portion axially separated from an aft portion. An aft frame is disposed at an aft end of the flow sleeve assembly. An annular flow sleeve extends from the aft portion of the support sleeve towards the aft frame. The flow sleeve includes a forward end that is axially separated from an aft end. The forward end of the flow sleeve circumferentially surrounds the aft end of the support sleeve. An annular impingement sleeve extends between the aft end of the flow sleeve and the aft frame. A forward end of the impingement sleeve is connected to the aft end of the flow sleeve, and an aft end of the impingement sleeve is connected to the aft frame.

Abstract: A heat resistant cast steel containing, in mass %, C: 0.05-0.15, Si: 0.03-0.2, Mn: 0.1-1.5, Ni: 0.1-1, Cr: 8-10.5, Mo: 0.2-1.5, V: 0.1-0.3, Co: 0.1-5, W: 0.1-5, N: 0.005-0.03, Nb: 0.01-0.2, B: 0.002-0.015, Ti: 0.01-0.1, Fe and unavoidable impurities. A method for manufacturing a heat resistant cast steel, the method including melting raw materials to obtain a molten metal, refining and degassing the molten metal, pouring the molten metal into a predetermined mold to form a shape, performing an annealing treatment at a temperature of 1000 to 1150° C., performing a normalizing treatment at a temperature of 1000 to 1200° C., performing a first stage tempering treatment at a temperature of 500 to 700° C., and performing a second stage tempering treatment at a temperature of 700 to 780° C.

Abstract: In the neighborhood area X of the tongue part 27 forming the winding end part of the scroll part 3, the wall part members 31 are provided on both the sides of the welding part (the facing part) ‘a’ of the first scroll part 5 and the second scroll part 7, wherein: the wall part members 31 encloses the welding part (the facing part) ‘a’ and forms the gas-tight space 33; and, the outer circumference wall which enclose the facing part and forms a gas-tight space configure a double-wall structure.

Abstract: The invention relates to a housing (1) of a radial flow compressor, comprising an intake pipe (4), a compressor duct (7) and an outlet pipe (5), wherein the housing comprises a housing body (basic construction) comprising at least an upper housing member (3) and a lower housing member (2) made of a fiber-reinforced thermoplastic polymer composition, and wherein the members (2, 3) are made, assembled together and fixed to each other in an integrated 2-step injection molding process.

Abstract: A compressor for compressing a gas, the compressor comprising: a housing having an axial inlet and an annular outlet volute; an impeller wheel including a plurality of blades, the wheel being rotatably mounted within the housing between the inlet and outlet volute; the axial inlet being defined by a tubular inducer portion of the housing and the annular outlet volute being defined by an annular diffuser passage surrounding the impeller, the diffuser having an annular outlet communicating with the outlet volute; the housing having an inner wall defining a surface located in close proximity to radially outer edges of the impeller blades which sweep across the surface as the impeller wheel rotates; wherein the compressor housing incorporates at least one section comprised of a deformable, energy absorbing material arranged to deform and absorb energy generated as a result of impeller wheel failure.

Abstract: A volute for a radial turbomachine is proposed. The turbomachine includes a radial compressor or a radial turbine. The volute is in particular for a radial compressor. The volute has a substantially annular cavity which is delimited at least by a first radial side surface. At least one substantially annularly circumferential groove is formed in the side surface.

Abstract: The sealing of a turbine casing is reinforced by decoupling a fastening flange from a remainder of a housing. The casing includes a body that is externally reinforced by axial ribs that are connected to an annular rib and the fastening flange is attached to the annular rib by an annular wall portion that is thinner than the annular rib and than the flange.

Abstract: A crossflow fan includes a rotary impeller formed by curved blades 42. Each of the blades 42 has an outer peripheral edge 43 close to the centrifugal side of the impeller and an inner peripheral edge 44 close to the rotation axis side of the impeller. A plurality of cutouts 45 are formed in the outer peripheral edge 43 and spaced apart at predetermined intervals. Dimples 48 for changing a boundary layer from a laminar flow to a turbulent flow are formed in a negative pressure surface 4q of each blade 42 in the vicinity of the outer peripheral edge 43 to prevent the gas flowing around the blade 42 from separating from the blade 42.

Abstract: A fan module, applied to a server including a first joint portion, includes a fan body, a first metal casing, a second metal casing and a plastic handle. The fan body includes an outlet surface, an inlet surface opposite to the outer surface, a first lateral surface and a second lateral surface. The first and second lateral surfaces are located between the outlet surface and the inlet surface. The first metal casing includes an air-through wall located on the outlet surface or the inlet surface, a first lateral wall connected to the air-through wall and mounted on the first lateral surface, and a metal handle connected to the first lateral wall. The second metal casing includes a second lateral wall mounted on the second lateral surface. The plastic handle, mounted on the second lateral wall, includes a second joint portion, for being engaged with the first joint portion.

Abstract: A gas turbine engine includes a compressor, a combustor section, and a turbine. The turbine includes an integrated case/stator segment that is comprised of a ceramic matrix composite material.

Abstract: A system and methods for applying a ceramic coating to a component that includes first applying a coating material to a first portion of a component. A removal agent is then applied to a second portion of the component that has an overspray byproduct thereon, and then the ceramic coating material is applied to at least the second portion of the component.

Abstract: A coupling support member including a pair of divided pieces is placed in a coupling part between a vane proximal end portion of a guide vane and an attachment flange, and the pair of divided pieces are joined to the vane proximal end portion from both the sides in the vane thickness direction. A groove is formed in one end portion joint surface of the coupling support member, a linear protrusion is formed on the other end portion joint surface, the vane proximal end portion is formed into a concavo-convex shape, a linear protrusion that is engaged with the groove which is formed in the end portion joint surface is formed on a joint surface to the one end portion joint surface, a groove that is engaged with the linear protrusion formed on the end portion joint surface is formed in the joint surface to the other end portion joint surface.

Abstract: A fan salt-fog-resistant structure and a fan frame thereof. The fan salt-fog-resistant structure includes a base seat having a bearing cup and at least one flow guide body. Multiple connection bodies outward extend from the base seat. The flow guide body is disposed at a junction between the base seat and the connection bodies. The fan frame includes a main body having a first open side and a second open side and a flow passage defined therebetween. One end of the connection body is connected with the second open side. When airflow entraining moisture and salt fog flows through the junction between the base seat and the connection bodies, the flow guide body serves to guide the airflow and prevent the airflow from forming eddy, whereby the salt fog entrained by the airflow will not crystallize to form sediments at the junction between the base seat and the connection bodies.

Abstract: A multi-component braze filler alloy comprising 60-70% by weight CM247 superalloy and BRB braze alloy is diffusion brazed to a CM247 alloy base substrate, such as a gas turbine blade or vane. The substrate/braze interface may be subsequently weld-repaired without de-melting and migrating the braze alloy from the interface. The weld zone and surrounding area are solidification crack resistant. After the alloy composition is brazed to the base substrate the component may be returned to service. Thereafter the component remains repairable by welding or re-brazing, if needed to correct future in-service defects.

Abstract: A submersible pump component is provided. The component includes a substrate including an outer surface in a plurality of orientations, wherein a first portion of the outer surface is configured to be worn by a first wear mechanism, and a second portion of said outer surface is configured to be worn by a second wear mechanism. The component also includes at least one layer of a first coating applied to the outer surface, and at least one layer of a second coating applied over said first coating at said second portion of said outer surface. The first coating is configured to inhibit the first wear mechanism at the first portion of the outer surface, and the second coating is configured to inhibit the second wear mechanism at the second portion of the outer surface.

Abstract: A multi-component braze filler alloy comprising at least 70% by weight MarM509A superalloy with the remainder MarM509B superalloy is diffusion brazed to a CM247 alloy base substrate, such as a gas turbine blade or vane. It is shown that generally higher braze temperatures lead to improved results including the possibility of re-welding such a brazed component, resulting in a re-repaired brazed component capable of continued commercial service.

Abstract: An annular fan case which covers an outer periphery of a fan in an aircraft engine includes: a case body including a first composite material containing a fiber and a resin; and a containment section including a second composite material containing a fiber and a resin, the containment section being formed on an outer periphery of the case body. A resin content of the containment section is set to be lower than the resin content of the case body.

Abstract: An aeroengine fan casing is made of composite material including fiber reinforcement densified by a matrix. The casing is secured to at least one ring or ring sector that is situated on the inside face of the casing and that is mechanically connected to an equipment fastener part that is situated on the outside face of the casing, in particular for fastening an accessory gearbox.

Abstract: A Ceramic Matrix Composites (CMC) airfoil for a gas turbine engine includes at least one CMC ply which defines a suction side, an outer platform, a pressure side and an inner platform with a continuous “I”-shaped fiber geometry.

Abstract: A hybrid airfoil for a gas turbine engine according to an exemplary embodiment of this disclosure can include a leading edge portion, a trailing edge portion, and an intermediate portion between the leading edge portion and the trailing edge portion. The leading edge portion can be made of a first material, the trailing edge portion can be made of a second material, and the intermediate portion can be made of a third material. At least two of the first material, the second material and the third material are different materials.

Abstract: An aluminum alloy turbine housing includes an inlet for exhaust, a turbine wheel space configured to receive exhaust via the inlet, a wastegate opening configured to receive exhaust via the inlet and to provide received exhaust to a wastegate chamber, and a locally hardened valve seat surrounding the wastegate opening. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.

Abstract: The invention relates to a turbine engine vane comprising a main body made of composite material, a leading edge, a trailing edge, and at least one metal structural reinforcement, the structural reinforcement comprising a junction surface portion connected to the main body, the structural reinforcement extending between the junction surface portion and one of the leading or trailing edges, the vane being characterized in that the profile of the junction surface portion of the structural reinforcement has a camber less than 30%.

Abstract: Aspects of the disclosure are directed to a system for an aircraft comprising: a titanium bottle section that includes at least two sections configured to house an engine, and at least one bifurcation panel coupled to the bottle section, wherein the at least one bifurcation panel includes a material that is different from titanium.

Abstract: There is provided a turbocharger bearing housing which is capable of reducing the weight thereof. A bearing housing of a turbocharger contains a shaft connecting a turbine and a compressor, and turnably supports the shaft. The bearing housing of the turbocharger is divided into a turbine-side housing disposed at a turbine side and a compressor-side housing disposed at a compressor side. The compressor-side housing is formed of an aluminum-based material.

Abstract: An impeller includes a hub, and a plurality of blades supported by the hub, the blades being arranged in at least two blade rows. The impeller has a deployed configuration in which the blades extend away from the hub, and a stored configuration in which at least one of the blades is radially compressed, for example by folding the blade towards the hub. The impeller may also have an operational configuration in which at least some of the blades are deformed from the deployed configuration upon rotation of the impeller when in the deployed configuration. The outer edge of one or more blades may have a winglet, and the base of the blades may have an associated indentation to facilitate folding of the blades.

Abstract: A method and apparatus are disclosed for a gas turbine spool design combining metallic and ceramic components in a way that controls clearances between critical components over a range of engine operating temperatures and pressures. In a first embodiment, a ceramic turbine rotor rotates just inside a ceramic shroud and separated by a small clearance gap. The ceramic rotor is connected to a metallic volute. In order to accommodate the differential rates of thermal expansion between the ceramic rotor and metallic volute, an active clearance control system is used to maintain the desired axial clearance between ceramic rotor and the ceramic shroud over the range of engine operating temperatures. In a second embodiment, a ceramic turbine rotor rotates just inside a ceramic shroud which is part of a single piece ceramic volute/shroud assembly.

Abstract: A support assembly and method for supporting an internal assembly in a casing of a turbomachine are provided. The support assembly may include a support member that may be slidably disposed in a recess formed in the internal assembly and configured to engage an inner surface of the casing. A biasing member may be disposed in a pocket extending radially inward from the recess. The biasing member may at least partially extend into the recess and may be configured to apply a biasing force to the support member disposed therein.

Abstract: A method of forming a fabric preform for a composite component from a fabric having a plurality of hoop tows is disclosed. One end of the fabric is received on the form such that the hoop tows of the fabric extend in a direction generally perpendicular to a central axis of the form. The fabric is wrapped around the form and at least some of the hoop tows are separated into hoop tow segments while the fabric is under a tension to enable a space to develop between ends of adjacent hoop tow segments along the length of the hoop tow. This separation of adjacent hoop tow segments accommodates increased deformation of the fabric during formation of the fabric preform while still maintaining a presence of hoop tow segments in at least portions of the fabric.

Abstract: Various turbine component preforms are disclosed having near-net shape features. In one embodiment, a turbine casing preform is disclosed. The turbine casing preform includes an as-cast body comprising a partially cylindrical wall section of a turbine casing, the wall section having an inner surface and an outer surface. The turbine casing preform also includes a circumferentially-extending vane slot formed in the wall section on the inner surface. In another embodiment, a turbine nozzle diaphragm preform is disclosed. The turbine nozzle diaphragm preform includes an as-cast body comprising a partially-cylindrical wall section of a turbine nozzle diaphragm having an inner surface and an outer surface. The turbine nozzle diaphragm preform also includes an as-cast, circumferentially-extending seal member projecting from one of the outer surface or inner surface.

Abstract: A composite fan case includes a composite fan case body having an outer surface. A bolt attachment is attached to the outer surface of the fan case and has an internal composite boss with at least one threaded metallic insert. The boss is attached to the outer surface of the fan case with a combination of fiber reinforced ply and adhesive. A bolt attachment and a method of attaching components to the outer periphery of the composite fan case are also disclosed.

Abstract: A turbo-molecular pump comprises: a case having a suction port and a flange; a rotor assembly housed inside the case, the rotor assembly having a shaft and a rotor integrated with the shaft with a fastening bolt, the rotor having a plurality of rotor blades formed thereon; a plurality of stator blades housed inside the case and arranged to face the rotor blades; and a plurality of spacers stacked along a peripheral surface of the case, the spacer fixing the stator blades. An anti-corrosion treatment is applied to a gas contacting section in a component that is provided on an evacuation upstream side with respect to an evacuation downstream side end of the first rotor blade from the evacuation upstream side and made of an alloy containing Fe or Cr.

Abstract: An turbocharger cartridge and engine cylinder head assembly includes a turbocharger cartridge that includes some but not all of the components of a turbocharger, while the engine cylinder head provides the components of the turbocharger that are not included in the cartridge. The cartridge includes a center housing rotating assembly having a shaft that joins a turbine wheel to a compressor wheel, the shaft passing through bearings housed in the center housing. The engine cylinder head defines a receptacle that receives the cartridge. The head also defines a diffuser and volute for the compressor, and a turbine volute. The cartridge defines a turbine nozzle and turbine contour, and further includes a wastegate unit as a part of the cartridge.

Abstract: An airfoil for a gas turbine engine includes an aft trailing edge support between a pressure side and a suction side.

Abstract: A CMC turbine stator blade 1 includes a blade 2 which is formed of a ceramic matrix composite material, and a band 11 which is formed of a ceramic matrix composite material or a metallic material and supports the blade 2. The blade 2 includes a first fitting portion 5 to which the band 11 is fitted at the outside thereof. The band 11 includes a second fitting portion 12 to which the first fitting portion 5 is fitted at the inside thereof. The CMC turbine stator blade 1 includes fixing means 6 which sandwiches the second fitting portion 12 from both sides in the height direction of the blade so that the blade 1 and the band 11 are fixed.