Abstract: A fan housing includes a housing body for accommodating fan components and an outer casing which surrounds the housing body in circumferential direction. The housing body has at least two webs extending in a circumferential direction on the radial outer side. The outer casing has at least two ribs extending in the circumferential direction on the radial inner side. The ribs, in the assembled state, between the housing body and the outer casing, form a channel circulating in the circumferential direction for receiving and holding a heating band. The outer casing has at least one guiding rib directed in the radial direction toward a housing body as well as into the channel and extending in the circumferential direction.

Abstract: A turbine or turbine system includes a compressor, a combustor, a turbine section, a diffuser with a parting line between two components, and a seal along the parting line. The seal includes a protrusion, a recess, and a flexible portion between the protrusion and the recess. The flexible portion has a bent cross-section perpendicular to the parting line. An outer surface of the bent cross-section contacts an inner surface of the recess. An inner surface of the bent cross-section contacts an outer surface of the protrusion. Sealing a parting line between two parts of a diffuser in a gas turbine system includes disposing a flexible portion between a protrusion and a recess of the two parts, contacting an outer surface of the bent cross-section with an inner surface of the recess, contacting an inner surface of the bent cross-section with an outer surface of the protrusion, and pressurizing the diffuser.

Abstract: A fan shroud assembly according to an example of the present application includes an air intake duct configured to receive ambient air, a fan configured to receive hot air, a motor driving the fan, and an air induction intake box in fluid communication with the fan and the air intake duct to mix the hot air and the ambient air. A vehicle and a method of providing cooling air to a vehicle engine are also disclosed.

Abstract: A centrifugal fan includes: an impeller; and a scroll housing surrounding the impeller, the scroll housing having suction hole and discharge hole formed therein. The scroll housing includes: a base plate; a scroll wall connected to the base plate, the scroll wall being formed in a scroll shape from a cutoff; and a discharge wall extending from the scroll wall. In the centrifugal fan, a flow path extending portion having a flow path sectional area extending toward an air flow direction convexly protrudes in the outer direction of the scroll housing in the base plate. Accordingly, a flow path is formed to extend in two directions including a direction in which the scroll wall extends and a direction in which the flow path extending portion protrudes. Thus, the static pressure of a discharge air current can be quickly recovered, and the blowing performance of the centrifugal fan can be improved.

Abstract: A turbomachine of the present disclosure includes a rotating shaft, an impeller, a bearing, and a casing. The casing is arranged around the impeller in a circumferential direction of the rotating shaft. A volute is defined in the casing as a passage of a working fluid that is compressed or expanded by rotation of the impeller. The casing includes one or more ribs. The one or more ribs are arranged only in a diagonal area, or the one or more ribs are a plurality of ribs and a degree of reinforcement of the diagonal area by the plurality of ribs is larger than a degree of reinforcement of a tongue portion area by the plurality of ribs.

Abstract: The turbine housing 1 is formed by sheet metal scroll members 5 and 7 butted opposite each other and welded together. A center core part 9 arranged in a central part of the scroll part 3 is integrally formed in one piece from a steel pipe member such as to include a housing portion 93 surrounding a turbine wheel 24, a bearing receiving portion 91 axially supporting the turbine wheel 24, and a plurality of circumferentially spaced supports 92 bridging a gap between the housing portion 93 and the bearing receiving portion 91.

Abstract: A duct liner includes a corner flanked by a pair of keyhole slots. An exhaust duct assembly includes an impingement liner received within a duct and a duct liner received within the impingement liner, the duct liner with a multiple of corners, each of the corners flanked by a pair of keyhole slots.

Abstract: A fan inlet diffuser housing system includes an air cycle machine, a housing coupled to the air cycle machine, an inlet fan disposed on the air cycle machine and configured to pass inlet air into the fan inlet diffuser housing, a center tube disposed in the housing, a diffuser cone disposed around the center tube, an inboard strut supporting the inner tube within the diffuser cone, and an outboard strut supporting the inner tube within the diffuser cone, the outboard strut being integral with the diffuser cone, wherein the inboard strut is coupled to the inner tube with a first plurality of mechanical fasteners, and the outboard strut is coupled to the inner tube with a second plurality of mechanical fasteners.

Abstract: A blower apparatus includes a blower casing; an elastic member for mounting a mounting portion that projects on an outer circumferential portion of the blower casing, to a blower support member disposed on the inlet side of the mounting portion; and a flange portion provided on the inlet side of the mounting portion. At least three elastic members are disposed in the same plane that is almost orthogonal to a rotation shaft, and adhesion surfaces are provided on both ends, in the rotation shaft direction, of each elastic member. The mounting portion is fixed to one of the adhesion surfaces, and the blower support member is fixed to the other of the adhesion surfaces. The flange portion is provided so as to oppose the blower support member through a gap having a thickness less than a thickness, in the rotation shaft direction, of the elastic member.

Abstract: An air turbine starter is provided and includes a rotor including turbine blades, which is rotatable about a rotational axis, a housing including a portion thereof radially surrounding the turbine blades to define a pathway along which fluids flow to interact with the turbine blades and a containment ring affixed to an exterior of the portion of the housing radially surrounding the turbine blades.

Abstract: An exhaust gas housing for a gas turbine is provided and includes a support structure, which, arranged concentrically, includes an outer ring and an inner ring which are interconnected by radially arranged struts, and a flow liner, which is attached inside the support structure and, arranged concentrically, includes an outer liner and an inner liner which are interconnected by radially arranged liner ribs. The liner ribs each encompass the struts of the support structure, and the outer and inner liners inside the support structure form an annular passage for the turbine's hot exhaust gases. The liner ribs are welded together from front and rear parts in the flow direction, forming welded seams which extend axially in the outer liner and in the inner liner up to the liner edge. End rings, which cover the welded seams at the liner edge, are welded on the liner's rear edges for reinforcement.

Abstract: The present invention provides an apparatus including a first metal component and a second metal component. The apparatus includes an interface between the first component and the second component, and a metal mesh interposed in the first interface. The apparatus further includes a composite component including a composite material. The composite component includes two portions, the first portion filling voids in the first interface and the second portion forming a structure that adjoins the first component and the second component. The metal mesh extends into the second portion of the composite component.

Abstract: A transfer tube including a tube member extends from a first end to a second end through an intermediate portion having an outer surface and an inner surface. The outer surface has an outside diameter. A flange is mounted at one of the first and second ends of the tube member. The flange includes a flange body extending from a first end portion to a second end portion through an intermediate section having an outer surface and an inner surface. The inner surface defines an inside diameter. The outside diameter of the tube member is between about 0.010-inch (0.0254-cm) and about 0.030-inch (0.0762-cm) smaller than the inside diameter of the flange.

Abstract: The present invention relates to an exhaust-gas turbocharger (1) having a turbine housing (2) and having a manifold section (3) which is connected to the turbine housing (2), wherein the turbine housing (2) and the manifold section (3) are formed as a single-piece cast part.

Abstract: A fabricated engine case has a plurality of circumferentially spaced struts radially extending between an outer case and an inner case. A mount apparatus is affixed to the outer case of the engine case. The mount apparatus is a mount base radially spaced apart from a circumferential skin of the outer case and a load bearing member extending radially inwardly to connect the mount base to an outer end of one of the struts.

Abstract: A method is provided for repairing a turbine nozzle assembly with an insert and a support structure. The method includes positioning the insert on the support structure of the turbine nozzle assembly; and plug welding the insert to the support structure of the turbine nozzle assembly.

Abstract: A steam turbine housing is provided having a housing wall and a stiffening cradle attached to the inner side which has two encircling inner webs which are arranged axially adjacent to one another and which project radially inward from the housing wall. Between the inner webs, running parallel and axially centrally, a central web is attached to the inner side of the housing wall, the radially inner edge of which is straight, wherein at the radially inner edge of the central web, the central web forks in a Y-shaped manner inward into two transition webs which extend to and merge into the adjacent inner web, such that the inner webs are fastened directly to the housing wall outside the circumferential extent of the transition webs and are fastened to the housing wall via the transition webs and the central web within the circumferential extent of the transition webs.

Abstract: A method of repairing a flange of a casing for an airplane turboprop or turbojet, in which the flange includes at least one through hole for passing a bolt for fastening equipment, and the hole opens out in a face of the flange that is worn by friction against the equipment, disclosed. The method includes mounting a bearing member on the flange. The bearing member includes a radial wall covering the worn face of the flange. The wall includes a hole that comes into register with the hole in the flange and having thickness for compensating the wear of the face of the flange. The member further includes an abutment for bearing against the periphery of the flange, and being fastened to the flange by adhesive.

Abstract: An exhaust case for a turbomachine includes, from outside towards inside, yokes, a collar and a hub, which are annular and coaxial. The hub is connected to the collar by radial arms and extends between an annular flange and an inner collar capable of guiding a gas flow. In the hub each arm includes a rib in a shape of a triangle which ends with the flange. The inner collar is extended into the hub by a plate capable of transferring forces between the flange and the yokes. The plate can be advantageously inclined with respect to a radial plane. Two portions, which enclose a cut-out formed in a minimum-stress region along the plate, are coupled with pre-set plays. The case is capable of absorbing compression and traction at a thermal gradient.

Abstract: A case assembly includes a plurality of segments, at least one braze joint, and one or more welds. The braze joint connects the plurality of segments together and the one or more welds extend across adjacent segments.

Abstract: An exhaust-gas turbocharger includes a bearing flange for securement of the exhaust-gas turbocharger to a bearing housing of a turbine wheel. The bearing flange is provided with an outer circumferential fin having a base portion which terminates in a free end. The base portion is defined by a width which is greater than a width of the free end. An outer housing is welded to the outer circumferential fin of the bearing flange, and accommodates an impeller housing.

Abstract: A fan housing includes a plastic casing having a skirt-board and a lateral wall. The skirt-board includes inner and outer peripheries spaced in a radial direction while the plastic casing further includes a first coupling portion formed along the inner periphery of the skirt-board. The lateral wall extends from a face of the skirt-board along the outer periphery of the skirt-board in an axial direction perpendicular to the radial direction. The fan housing includes a metal frame having a shaft coupling member and a second coupling portion. The second coupling portion of the metal frame is coupled to the first coupling portion of the plastic casing. A motor can be mounted to the metal frame of the fan housing, and an impeller can be rotatably coupled to the motor to form a heat dissipating fan.

Abstract: A double-walled turbocharger housing made of sheet metal includes an inner sheet metal shell which conducts hot exhaust gases and a relatively cold outer sheet metal shell which is spaced apart from the inner sheet metal shell via an air gap. The double-walled turbocharger housing is connected to a bearing flange with a circumferential collar via a common welding seam. The bearing flange is provided with a collar on an outside which faces away from the hot exhaust gas. An outer end of the inner sheet metal shell is provided with a collar with which it embraces the outer sheet metal shell. Both sheet metal shells are connected with the collar of the bearing flange via a common welding seam, wherein an air gap is present between the inner sheet metal shell and the outer sheet metal shell up to the outer end of the inner sheet metal shell.

Abstract: A gas turbine engine case having a working fluid flow, includes inner and outer case portions defining an annular duct for directing the working fluid flow, and a plurality of struts positioned within the annular duct and extending between the inner and outer case portions. The struts are welded to the inner and outer case portions with a first weld along a peripheral line of the respective struts and with second weld, of fillet type, in selected locations for additionally connecting a portion of each strut to the respective inner and outer case portions.

Abstract: A steam turbine apparatus is disclosed. In one embodiment, the steam turbine apparatus comprises: an exhaust shell portion including: a first section having a semi-circular cross-section; an exhaust section contiguous with the first section, the exhaust section including an intermediate-pressure exhaust outlet; and a second section having an oblate spherical cross-section including a substantially flattened portion, the second section configured to fluidly connect with the first section, wherein the first section and the second section form a continuous steam flow path.

Abstract: A stator blade ring is provided with which the possibilities of thermal deformation and a decrease in strength can be reduced, the shape flexibility can be ensured, and the compression performance can be improved. It includes stator blade segments (21) in each of which an inner shroud portion (31) and an outer shroud portion (29) divided corresponding to one stator blade (27) are provided at both ends of the stator blade (27) so as to be formed as a single part, and connecting members (23) that are formed of arch-shaped plates and are disposed on at least one of the inner shroud portions (31) and the outer shroud portions (29) of the stator blade segments (21) adjoining in a circumferential direction, on a side opposite to the stator blades (27). The stator blade segments (21) are welded to the connecting members (23) at a portion of the length thereof in the circumferential direction.

Abstract: An inlet assembly for an aircraft engine nacelle includes an inner barrel, an outer barrel radially spaced from the inner barrel, and a rear support for supporting the outer barrel relative to the inner barrel. The rear support includes at least one radially extending stiffener and at least one energy absorber defining a zone of deformation adjacent the inner barrel. The rear support is deformable in the zone of deformation in response to forces applied during a fan blade-out event to prevent fracture of the rear support.

Abstract: A cooling apparatus comprising an impeller, a housing that encloses the impeller, an inlet opening formed between the hosing and impeller and a projection formed on the housing that extends from the housing towards the impeller.

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 multi-shell turbine casing system comprises at least one supporting cell joined to at least one retaining cell. The at least one supporting cell has at least one supporting cell wall and at least one truss section. The at least one retaining cell has at least one retaining cell wall. According to the invention, the at least one supporting cell wall and the at least one retaining cell wall form an outer shell and an inner shell. In an exemplary embodiment, the at least one truss section is oriented to provide support for the inner shell and is a triangular truss comprising cylindrical members joined by plate-type or box-type connectors. An exemplary truss section includes a plurality of horizontally oriented stabilizers joining the vertically oriented member to the outer shell. A multi-shell casing system may include additional truss sections, which may be joined to one another and to adjacent structure.

Abstract: A screw pump includes a pump housing on which a flange section for installing the pump is formed. The screw pump further includes an integrated pressure limiting valve. The pressure limiting valve in the flange section of the pump housing is installed in the pump housing.

Abstract: A method for producing a turbine casing for a rotating machine is provided. The casing is manufactured by a casting process, and is cast in two casing halves which are separated by a parting plane which passes axially through the turbine casing. Each casing half is first cast in one piece in each case, and each casing half is separated into at least two casing sections which are joined together for forming a casing half in each case.

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: A cowl for an aircraft engine, and processes for producing the cowl to have a layered construction and a high temperature capability. The layered construction of the cowl includes a core member having a cellular construction comprising internal hollow cells, and first and second skins brazed to edges of the cells at opposite surfaces of the core member. The first and second skins and the core member are formed of titanium alloys, the first and second skins are brazed to the core member, and the layered construction of the cowl lacks a thermal insulation capable of thermally protecting the second skin and brazed joints that attach the second skin to cell wall edges at the second surface of the core member.

Abstract: Described is reinforcement of a fan case in a gas turbine jet engine. In one embodiment, a containment ring and a hear resistance ring 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. In one example, the containment ring is made of a sue alloy to provide added strength to the fan case should a fan blade break, containing the fan blade within the fan case. Also, the containment ring may extent forward of at least the leading edge of each fan blade and aft of at least the trailing edge of each fan blade. The heat resistance ring is made of titanium or other suitable material. Additionally, one or more stiffener rings may be shrink interference fit on the outside diameter of the fan case.

Abstract: One embodiment of the present invention is a unique gas turbine engine case. Another embodiment is a unique method of manufacturing a gas turbine engine case. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engine cases. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Abstract: A method of repairing an engine case for a gas turbine engine includes the steps of identifying a damaged flange on an engine case, removing the damaged flange down to a surface of the engine case to receive a replacement flange. The replacement flange is placed on the surface, and welded to the surface utilizing cold metal transfer.

Abstract: A method of joining a first part together with a second part is disclosed. The method may comprise providing a first part having a first joining portion including a first channel and a second part having a second joining portion including a second channel. The method may further comprise positioning the first part adjacent to the second part such that the first channel and second channel align with one another to define a cavity. The method may still further comprise preparing a mixture comprising at least one of a metal powder and a polymer binder, placing the mixture into the cavity so as to form a preform and solidifying the preform forming a metal element in the cavity. The metal element joins the first part together with the second part.

Abstract: A lanced and/or slit seamed housing and method of manufacture having a peripheral rolled and lanced or punched seam between a wrapper and the housing panels. The method of manufacture utilizes similar or dissimilar sheet materials in a variety of material thicknesses and with or without coatings applied prior to formation whereby a housing is formed quickly and safely. The rolling and lancing method manufactures a blower housing with an assured and positive sealed seam between the panels and wrapper of the housing. The lances or slits maintain the integrity of the seam and prevent slippage between the wrapper and panels.

Abstract: The present invention relates to a nacelle for a turbojet, comprising an air inlet structure capable of channelling a flow of air to a turbojet fan and a middle structure (5) comprising a casing (9) designed to encircle said fan, with the air inlet structure attached to it, said structure having a peripheral inside surface at least partly equipped with a sound-attenuating structure (13) extending without geometrical interruption around at least part of the casing, said structure being characterized in that a gap (14) is provided between the sound-attenuating structure and the casing.

Abstract: A fan unit has a fan (10). Associated with the fan is an air-guiding tube (22) through which the fan (10) transports air, during operation. The air-guiding tube (22) is connected to at least one carrier tube (23) for suspension of the fan (10). The fan includes a carrier part (25). A damping member (30) is arranged between the carrier part (25) and the carrier tube (23) to reduce any structure-borne sound which occurs during operation of the fan (10).

Abstract: A groove 50 formed in each stator ring segment piece 41 is formed to have side wall portions 50b on opposite sides inclined with respect to a bottom 50a so that a width of the groove 50 gradually decreases from an outer peripheral side toward the bottom 50a. A coupling member 42 has a sectional shape so as to have a maximum width at protrusions 42b at an intermediate portion in a thickness direction. The protrusions 42b on the opposite sides abut against or approach the side wall portions 50b of the groove 50 when the coupling member 42 is placed in the groove 50, a space 100 is formed on the side of the bottom 50a of the groove 50, and a welding groove 200 having a substantially V-shaped section is formed on the side remote from the bottom 50a of the groove 50.

Abstract: Gas turbine airfoil assemblies and methods of repair are provided. In this regard, a representative method includes: separating the airfoil from the platform; forming a depression in the platform, the depression being sized and shaped to receive a replacement airfoil; and affixing the replacement airfoil within the depression such that the replacement airfoil is attached to the platform.

Abstract: A fan frame structure includes 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.

Abstract: A method of repairing a case for a gas turbine engine includes identifying areas of damage on its internal holding structures in a gas turbine case, and utilizing cold metal transfer to deposit weld material to the internal holding structures.

Abstract: A blower including a blower volute, a blower motor, and a fan wheel. The blower motor is disposed at the top of the blower volute. The fan wheel is disposed inside the blower volute and connected to the blower motor. The blower volute comprises an air inlet, an air outlet, a cover body, and a bottom cover. A plurality of installation parts is disposed at an outer side of the cover body. The bottom cover and the cover body are embedded with each other and welded together or stuck together. The blower has a simple connection structure, high generality, friendly installation, and low cost.

Abstract: A case for a gas turbine engine includes a single-piece case that includes a combustor case portion and a turbine case portion that is integrally formed with the combustor case portion as one piece. In one example, the single-piece case includes a transition duct/mid-turbine frame case portion is integrally formed with the combustor and turbine case portions.

Abstract: An intermediate housing floor for a fluid kinetic machine is provided. The intermediate housing floor includes a partial joint at which the intermediate housing floor may be divided during installation and/or removal into/from the fluid kinetic machine and is made up of at least two overlapping partial joint surfaces at sections of the intermediate housing floor that face one another. A recess is provided in the area of the overlap in at least the one partial joint surface, a coating is kept in the recess. The coating protrudes from the one partial joint surface as a protrusion in the removed state of the intermediate housing floor in which the intermediate housing floor is divided at the partial joint so that in the installed state of the intermediate housing floor the coating abuts against the other partial joint surface facing the one partial joint surface, whereupon the partial joint is sealed.

Abstract: A method and apparatus for controlling distortion in the casing of a gas turbine are disclosed. The method uses a split in the flange ID underneath “false” flanges to tune the hoop stiffness of the casing to match the stiffness and behavior of the bolted joint. By matching the hoop carrying capability and load path of the split-line flange, as well as the thermal mass effect, the distortion can be channeled to a higher order distortion mode that can evenly distribute the deflection and approach a pure circular form.

Abstract: A casing includes an upper casing and a lower casing jointed in a dividable manner, and a sealing structure that suppresses outward leakage of gas from a joint area between the upper casing and the lower casing. The casing 1 also includes: an upper protruding element that protrudes from an outer circumference of the upper casing; a lower protruding element that protrudes from an outer circumference of the lower casing; and an intermediary member that is arranged on outer circumferences of the upper protruding element and the lower protruding element. The joint area between the upper casing and the lower casing is extended by the upper protruding element and the lower protruding element, and the intermediary member is welded to the upper protruding element and the lower protruding element, at a position offset from the joint area.