Abstract: To be provided is a vacuum pump reducing the influence of thermal expansion of connector pins to prevent cracks in soldered parts while preventing damage to electronic elements. Pins 207 linearly expand with the heat accumulated in a bottom space 301. The bottom space 301 is heated quite easily since it is in a vacuum environment. A screw 235A is arranged near the left edge of an AMB control substrate 209. Since no screw is arranged on the right of the screw 235A, the AMB control substrate 209 is released toward the right. When the pins 207 expand with heat, the AMB control substrate 209 bends by an angle ?2 from the screw 235A as a fulcrum, but this bend angle is gradual, which means that the possibility of causing cracks in solder connection parts between the AMB control substrate 209 and the pins 207 is extremely small. Since deforming pressure of the AMB control substrate 209 is reduced, influence on the electronic elements can be reduced correspondingly.

Abstract: To be provided is a vacuum pump having substrates which can be wired together easily and cooled easily. A substrate unit structure is formed by covering the opening of the casing of the pump main unit 100 with the plate 201 functioning also as the casing of the control unit 200. Pins 207 of a terminal 210 fixed while penetrating the plate 201 are soldered directly to an AMB control substrate 209 and an aerial connection substrate 211 in order to integrate these components. Therefore, the casing and sealing structures can be made simple. Accordingly, a drip-proof structure can be made with the terminal 210 at low cost without using expensive drip-proof connectors 1 and 3. Further, by cooling the plate 201, electronic components mounted respectively on the AMB control substrate 209 in a vacuum atmosphere and the aerial connection substrate 211 in an air atmosphere can be cooled simultaneously.

Abstract: A casing is provided having a longitudinal axis of a turbomachine, the axis extending along a rotor. The casing includes at least one jacket part extending along the longitudinal axis and at least one end-face cover. The cover is surrounded by the jacket part at least with a part of the axial extension of the cover. In order to reduce the need for radial clearance, without compromising the availability or safety of the operation of the machine, the cover has radial clearance with respect to the jacket part and at least two separate guide elements of the cover are provided on the jacket part in two different circumferential positions with respect to the longitudinal axis. The respective guide elements are designed such that they block a respective movement of the cover in the circumferential direction at least unidirectionally.

Abstract: According to one aspect of the invention, a turbine assembly includes a first component, a second component circumferentially adjacent to the first component, wherein the first and second components each have a surface proximate a hot gas path and a first side surface of the first component to abut a second side surface of the second component. The assembly also includes a first slot formed longitudinally in the first side surface, a second slot formed longitudinally in the second side surface, wherein the first and second slots are configured to receive a sealing member, and a first groove formed in a hot side surface of the first slot, the first groove extending axially from a leading edge to a trailing edge of the first component.

Abstract: A fan impeller structure includes an annular body. The annular body has a top section and a receiving space. At least one first bending section is formed between the top section and the annular body. At least one recess is formed at the first bending section. At least one flow guide hole is formed between the first bending section and the recess in communication with the receiving space. In operation, the airflow conducted into the receiving space is increased. Moreover, no matter whether the fan impeller structure is clockwise rotated or counterclockwise rotated, the airflow can be conducted into the receiving space through the flow guide hole. Accordingly, the heat dissipation effect will not be affected by the rotational direction of the fan impeller structure.

Abstract: An exemplary heat dissipating fan includes a frame and an impeller rotatablely received in the frame. The frame includes a base and a top cover disposed on the base, the base includes a bottom plate a peripheral sidewall. The sidewall extends between the bottom plate and the top cover, and the base and the top cover cooperatively defines a receiving space. The impeller is rotatably received in the receiving space. The top cover, the bottom cover and the sidewall cooperatively defines an air inlet therebetween. The top cover, the bottom plate and the sidewall cooperatively defines an outlet therebetween. The air outlet is generally adjacent to and substantially perpendicular to the air inlet.

Abstract: During engine braking of a turbocharged internal combustion engine, the exhaust gas pressure increases and this is used to pressurize the seals between the turbocharger shaft and the bearing housing so as to prevent oil leakage into the compressor housing. Immediately after engine braking, stored exhaust gas pressure is used to pressurize the seals at the turbine end so as to prevent oil leakage into the turbine housing. In an alternative arrangement the exhaust gas is used to generate a reduced pressure in the bearing housing to increase the pressure gradient across the seals.

Abstract: The present teachings relate to an air feed device with at least one impeller; with at least one housing that at least partially surrounds the impeller, with at least one intake opening for inward suction of air into an operating space of the impeller, with at least one opening to blow out air from the operating space of impeller. Provision is made that the air feed device has at least one additional through-passage opening for air.

Abstract: A fan assembly includes a fan including a board defining a number of through hole, a dustproof member attached to an outer surface of the board, and a number of fasteners. The dustproof member defines a number of fixing legs. Each fastener includes a head abutted against a corresponding one of the fixing legs such that the corresponding leg is sandwiched by the head and the outer surface of the board, a pole extending from a side surface of the head to extend into a corresponding one of the holes, a hook extending in the same direction as the pole from an edge of the head, a projection extending toward the pole from a distal end of the hook and engaged with an inner surface of the board opposite to the outer surface.

Abstract: A floor standing pedestal fan for creating an air current includes a base housing an impeller and a motor for rotating the impeller to create an air flow, an air outlet, and a telescopic duct for conveying the air flow to the air outlet.

Abstract: Braze materials, brazing processes, and coatings produced therefrom, for example, a wear-resistant coating suitable for protecting surfaces subjected to wear at high temperatures. The braze material includes first particles formed of a metallic alloy and second particles formed of a cobalt-base braze alloy having a melting point below the melting point of the first particles. The braze alloy consists of, by weight, 3.5 to 15.0% silicon, 2.0 to 6.0% boron, and the balance cobalt and incidental impurities, and the second particles constitute at least 30 up to 90 weight percent of the first and second particles combined. Following a brazing cycle performed on the braze material, a wear-resistant coating is formed in which the first particles are dispersed in a matrix of the braze alloy.

Abstract: A shroud segment for a gas turbine engine, the shroud segment constructed from a composite material including reinforcing fibers embedded in a matrix, and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces, wherein the inner wall defines an arcuate inner flowpath surface; and wherein a compound fillet is disposed at a junction between first and second ones of the walls, the compound fillet including first and second portions, the second portion having a concave curvature extending into the first one of the walls.

Abstract: A shaping apparatus for shaping a workpiece. The apparatus comprises first and second pairs of shaping members and a spacer located between the first and second pairs of shaping members. The first pair of shaping members comprises a material having a first linear coefficient of thermal expansion, and the second pair of shaping members comprises a material having a third linear coefficient of thermal expansion. The first linear coefficient of thermal expansion is higher than the second linear coefficient of thermal expansion such that on heating of the apparatus, thermal expansion of the shaping members causes the first pair of shaping members to expand outwardly, and the second pair of shaping members to expand inwardly.

Abstract: The method is used for making an annular gas turbine engine case from a preform. The method comprises comprising flowforming at least one section of the preform, and then outwardly bending at least one portion of the perform.

Abstract: A gas turbine engine includes a fan section with twenty (20) or less fan blades and a fan pressure ratio less than about 1.45.

Abstract: A method and structure negating thermal inertia of a solid portion, such as shielding, which influences mechanical behavior of parts of an engine structure, by reducing forces transmitted to the engine structure during an event in which a turbine blade ruptures, while preserving mechanical strength and vibratory positioning. The structure includes a flexible fastener for a shield, enabling producing a fusible section. An assembly for mounting a shielding onto a casing of the engine structure of a turbine includes connection lugs and points for attachment to the casing and shielding. The attachment points are sufficiently spaced apart in accordance with curvature of the shielding and casing so connection between the lugs and the shielding or casing, and connection of the attachment points, are substantially tangential. The lugs are sized so the connection has sufficient flexibility to control vibratory positioning thereof and ensure sufficient mechanical strength under thermo-mechanical loads.

Abstract: An exemplary component manufacturing method includes scanning a first surface of a component to determine a location of pocket surfaces of the first surface. The method machines apertures in the component from a second, opposite surface of the component. The apertures each have a cooling air inlet within one of the pocket surfaces and a cooling air outlet within the first surface.

Abstract: A steam supply for a turbomachine with an inner housing and an outer housing is provided. The steam supply includes an inner pipe and an outer pipe, a cooling medium inlet opening disposed in the outer pipe and a cooling medium entering thereby into space between the inner pipe and the outer pipe, and the inner pipe being cooled thereby.

Abstract: A turbocharger (1) having a turbine housing (2), a compressor housing (3) which has a compressor outlet (20), and a silencer (21) which is arranged on an end region (22) on the compressor outlet (20) and which has a silencer housing (23) in which an insert part (25) is arranged so as to form at least one buffer chamber (24) which is connected via at least one opening (26) to an air-guiding duct (27). The opening (26) has an edge (28) with a radially inner corner (29) which is designed so as not to have a sharp edge.

Abstract: A nozzle for a fan assembly has an air inlet, an annular air outlet, and an interior passage for conveying air from the air inlet to the air outlet. The interior passage is located between an annular inner wall, and an outer wall extending about the inner wall. The inner wall at least partially defines a bore through which air from outside the nozzle is drawn by air emitted from the air outlet. The inner wall is eccentric with respect to the outer wall so that the cross-sectional area of the interior passage varies about the bore. The variation in the cross-sectional area of the interior passage can control the direction in which air is emitted from around the air outlet to reduce turbulence in the air flow generated by the fan assembly.

Abstract: A water drainage system for a blower, including a shell body (1) and a shell cover (2). The shell body (1) is fitted with the shell cover (2) to form a cavity (3) in which a wind wheel is arranged. A side wall of the shell body (1) is protruded to form a wind pipe (4) which is connected to the cavity (3). The wind pipe (4) is provided with a water outlet (41).

Abstract: A nacelle for a turbojet engine is provided that includes an air intake upstream from the turbojet engine, a middle section intended to surround a fan of the turbojet engine and its case, and a downstream section. The middle section is made from at least one aerostructure capable of ensuring external aerodynamic continuity of the nacelle, and the aerostructure is rigidly bound, so as to be able to be taken apart, to at least one surrounding fixed structure.

Abstract: A hypereutectic chromium alloy consisting of 9 to 12 at % tantalum, 4 to 15 at % silicon, 0 to 7 at % molybdenum, 0 to 7 at % aluminium, 0 to 7 at % titanium, 0 to 5 at % rhenium, 0 to 2 at % silver, 0 to 2 at % hafnium, 0 to 2 at % lanthanum, 0 to 2 at % cerium, 0 to 2 at % yttrium and the balance chromium and incidental impurities. The hypereutectic chromium alloy has good oxidation resistance and good fracture toughness. The chromium alloy may be used to make gas turbine engine turbine blades, turbine vanes, turbine seals, combustion chamber tiles, exhaust nozzle segments or steam turbine components.

Abstract: An anti-relief fan frame body structure includes a frame body and multiple anti-relief sections. The frame body has a receiving space and a shaft seat received in the receiving space. The frame body further has multiple flow guide members extending from a circumference of shaft seat to an inner circumference of the frame body to connect with the inner circumference of the frame body. The anti-relief sections are disposed on the inner circumference of the frame body between the flow guide members to increase the performance of the fan.

Abstract: A flexible seal system for a gas turbine engine includes an annular mounting bracket, an annular support bracket, an annular flexible seal and a plurality of mounting spacers. The flexible seal extends axially between a first mounting segment and a second mounting segment. The first mounting segment is connected axially between the mounting bracket and the support bracket, and includes a plurality of mounting apertures that extend axially through the first mounting segment. Each of the mounting spacers is arranged within a respective one of the mounting apertures, and extends axially between the mounting bracket and the support bracket.

Abstract: A shroud apparatus for a gas turbine engine includes: an annular shroud segment having an arcuate bottom wall defining an arcuate inner flowpath surface, spaced-apart forward and aft walls extending radially outward from the bottom wall, and spaced-apart side walls extending radially outward from the bottom wall and between the forward and aft walls, each side wall defining an end face which includes: an axial slot extending in a generally axial direction along the end face; a first radial slot extending in a generally radial direction along the end face, and intersecting the axial slot; an axial spline seal received in the axial slot; and a first radial spline seal having an L-shape with radial and axial legs, the radial leg being substantially longer than the axial leg, wherein the radial leg is received in the first radial slot, and the axial leg is received in the axial slot.

Abstract: A guiding apparatus for guiding a flow of a fluid for use with a rotor, the rotor comprising an annular radial vane assembly surrounding a central space which is enclosed save via the vane assembly and being arranged to rotate about a vertical axis, the guiding apparatus comprising a screening for guiding the fluid to circulate substantially about the vertical axis within the central space in the same direction as the rotor during use.

Abstract: A fan cover includes a base plate, a frame, and a number of ribs. The frame is made of a number of ring-shaped portions with different diameters and concentrically arranged. A number of strip-shaped portions are radially formed among the ring-shaped portions to connect the ring-shaped portions together. The ribs connect the frame to the base plate at an angle. A number of ventilation holes are defined in the frame.

Abstract: A centrifugal fan comprises an impeller and a casing. The impeller includes a hub and a plurality of blades. The casing comprises an upper casing, a lower casing, at least one protrusion, a first inlet opening and a second inlet opening. The lower casing is disposed opposite to the upper casing and connected to the upper casing to form an accommodation room for receiving the impeller. The protrusion is formed on the upper casing and/or the lower casing inside the casing and immediately surrounds the blades. The first inlet opening is defined on the upper casing and comprises a primary inlet opening augmented by a secondary inlet opening. The second inlet opening is defined on the lower casing. The protrusion surrounds the first inlet opening and/or second inlet opening.

Abstract: A fan module includes a fan body and a cover. The fan body defines a mounting hole. The cover is secured to the fan body and includes a spoke and a hook extending from the spoke. The hook includes a connecting portion and an elastically deformable latching portion. The connecting portion is connected to the spoke. The elastically deformable latching portion extends from the connecting portion. The connecting portion is received in the mounting hole. The elastically deformable latching portion is engaged with the fan body.

Abstract: A turbomachine blade or vane of composite material comprising fiber reinforcement densified by a matrix is fabricated by a method comprising: making a one-piece fiber blank by three-dimensional weaving; shaping the fiber blank to obtain a one-piece fiber preform having a first portion forming a blade airfoil and root preform and at least one second portion forming a blade platform preform; and densifying the preform with a matrix to obtain a composite material blade or vane having fiber reinforcement constituted by the preform and densified by the matrix, forming a single part with at least one incorporated platform.

Abstract: The present application thus provides a seal assembly for a turbine. The seal assembly may include a number of metal shim layers and a number of non-metallic layers. A pair of the non-metallic layers surrounds each metal shim layer.

Abstract: A system for transferring molten metal from a vessel and into one or more of a ladle, ingot mold, launder, feed die cast machine or other structure is disclosed. The system includes at least a vessel for containing molten metal, an overflow (or dividing) wall, and a device or structure, such as a molten metal pump, for generating a stream of molten metal. The dividing wall divides the vessel into a first chamber and a second chamber, wherein part of the second chamber has a height H2. The device for generating a stream of molten metal, which is preferably a molten metal pump, is preferably positioned in the first chamber. When the device operates, it generates a stream of molten metal from the first chamber and into the second chamber. When the level of molten metal in the second chamber exceeds H2, molten metal flows out of the vessel and into another structure, such as into one or more ladles and/or one or more launders.

Abstract: The invention aims at achieving a mounting of a turbomachine stator blading while avoiding a delicate machining process of the engine casing. It also aims at simplifying the mounting as well as at reducing the costs, and at decreasing the number of item references for the engine. To achieve these objects, the invention uses an extension of the engine casing. A turbomachine comprises at least one stator blading for air or gas stream flowing on the internal engine casing. The stator blading comprises a rim which is assembled on a radial extension of engine casing with axial fastening means. In a preferred embodiment of the turbomachine, the engine casing presents an annular wall provided with fingers originating axially from this wall and extending according to a curvature so that they present a radial extension tip against the rim of the stator blading.

Abstract: The invention relates to a drum motor comprising: a drive unit, such as a rotor/stator unit of an electric motor, or a hydraulic or pneumatic actuator unit, an output shaft connected to the drive unit for transmitting force and torque, an outer drum, which surrounds the output unit at least partially and is rotatably mounted relative to a fastening axis, and a casing, which is connected to the outer surface of the rotatable drum and has a profile. According to the invention, the profile contains a helical groove (40) in the casing that extends over at least part of the surface of the casing and runs helically about the rotational axis of the rotatable drum.

Abstract: The disclosure relates to a high temperature mechanical system, such as a gas turbine engine, including a first coating deposited on a first substrate and a second coating deposited on a second substrate. The first coating includes a first bond layer, a second bond layer, and a first ceramic outer layer, wherein the second bond layer is between the first bond layer and first ceramic outer layer. The second coating includes a third bond layer deposited on the substrate and a second ceramic outer layer deposited on the third bond layer. The second coating is configured to abrade the first coating, e.g., during operation of the high temperature mechanical system.

Abstract: The air-blow working machine comprises a fan provided in a fan casing and a drive unit to drive the fan, and discharges an airflow generated by the rotating fan. The fan casing has an inner wall disposed between the fan and the drive unit. A smooth surface is formed on the face of the inner wall on the side of the fan. A first concavo-convex portion is formed on the face of the inner wall on the side of the drive unit. Thereby, a noise is reduced without an influence upon performance for blowing air.

Abstract: A self-adjusting device (25) for controlling the clearance (C), especially in the radial direction, between rotating and stationary components (21, 23) of a thermally loaded turbo machine, changes clearance (C) in a linear and/or non-linear way during transition of the machine between standstill and steady-state operation. Simple and effective control can be achieved, even in the case of a nonlinear variation of the clearance during transitional operation, by the self-adjusting device (25) including at least two different driving elements (A, B) to move the rotating and fixed components (21, 23) relative to each other in order to change the clearance (C) between them, and by the different driving elements (A, B) being configured to be activated at different times during the transition of the machine.

Abstract: A ring fluid foil including a modified trailing portion for a shrouded fluid turbine and shrouded fluid turbine including such ring fluid foils are described herein. The modification of the trailing portion increases flow turning by the fluid foil without, or with reduced, boundary layer separation on a suction side of the fluid foil.

Abstract: A fan enclosure that has manifolds connected to the inlet and outlet of the fan that provides an airtight connection. The manifolds, once connected to the enclosure, provide a pass through of the enclosure for the fan, thereby not requiring the enclosure to be pressurized. A condensate bypass can be installed both on the discharge manifold and the fan impeller body. Both condensate bypasses can be piped to the inlet manifold, preventing moisture accumulation in the fan and the enclosure. The fan enclosure helps prevent contamination and explosive gas in the air stream from coming in contact with the fan motor's electrical components and bearings. The fan enclosure reduces the contamination of the impeller bearing, does not draw or push air through the electrical conduit connected to the enclosure, and the enclosure is not required to be airtight to preform properly.

Abstract: The axial-flow turbine includes an extraction chamber 15 disposed on the outer circumference of a turbine blade chamber 12 and an extraction opening 16. An outer diaphragm 8 forming the downstream-side wall surface of the extraction chamber 15 is provided with a projection 21 formed more radially inwardly than the downstream-side edge on the outer circumference of an adjacent bucket 2 on the upstream side of the extraction opening 16 to form the downstream-side wall surface of the extraction opening 16. The projection 21 forms an upstream-side wall surface 18 of the outer diaphragm 8 for leading a part of the working fluid to the extraction chamber 15, and an inner wall surface 19 of the outer diaphragm 8 for leading the remaining working fluid to a bucket 11 on the downstream side of the extraction opening 16.

Abstract: An intake charged pump for pumping liquid and which has an intake duct that extends to the suction area of the pump. The pump has a duct through which a jet stream flows to the suction area. A nozzle arrangement in the intake duct accelerates the liquid which is returned via the jet stream and supports the suction of a suction stream of the liquid from a storage container. A nozzle of the nozzle arrangement leads into the mixing chamber at an acute angle in a such way that the jet stream, leaving the nozzle, creates a common mixing stream with the suction stream from the storage container, and through which partial streams having essentially the same pressure and energy content, can be delivered to the front and back suction pockets of the double chamber pump.

Abstract: A strip seal for providing a seal between adjacent components, which include a first groove and a second groove angled with respect to and intersecting the first groove. The grooves of respective components are opposed to one another when the components are assembled. The strip seal includes a first strip section to span between and be received in the opposed first grooves, and a second strip section to span between and be received in the opposed second grooves. One end of the first strip section is arranged to butt against the second strip section at the intersection of the grooves. The other end of the first strip section has at least one deformable projection that can engage the end of the first groove. The projection deforms as it engages the end of the groove and urges the end of the first strip section against the second strip section.

Abstract: A system is provided including a turbine exhaust section. The turbine exhaust section includes an exhaust flow path. The turbine exhaust section also includes an outer structure having an outer casing, an outer exhaust wall disposed along the exhaust flow path, and an outer cavity disposed between the outer exhaust wall and the outer casing. The turbine exhaust section further includes an inner structure having an inner exhaust wall disposed along the exhaust flow path, an inner cavity disposed between the inner exhaust wall and an inner casing, and a bearing cavity disposed between the inner casing and a bearing housing. In addition, the turbine exhaust section includes a strut extending between the outer structure and the inner structure. The strut includes a first flow passage configured to flow a fluid from the inner cavity to the outer cavity.

Abstract: Systems for increasing the efficiency of a turbine and an overall power plant system are disclosed. In one embodiment, a turbine includes: an outer shell including a set of grooves configured to complement components of a wheel and diaphragm steam path section; a drum rotor disposed within the outer shell; a set of shell converts connected to the outer shell via the set of grooves, the set of shell converts configured to complement components of the drum rotor; and a working fluid passage substantially defined by the drum rotor and the set of shell converts.

Abstract: A device for preventing rotation of a segment of nozzle guide vanes assembly in a form of an annulus sector housed inside an annular casing of a turbo machine with interposing of a heat shield sheet between an internal wall of the casing and an external wall of the segment of nozzle guide vanes assembly, the device including a rotation-proofing peg fitted both into a notch formed in the segment of nozzle guide vanes assembly and in a housing formed in the casing, the heat shield sheet including a tab resting against the rotation-proofing peg. A surface portion radially between the tab and the internal wall of the casing forms an end stop in event of a possible radial movement of the heat shield sheet while the turbo machine is in operation.

Abstract: A housing for use in an air machine includes a housing body for housing at least one rotor. The housing body has at least one conduit for connection to a connecting conduit. The conduit has a drain hole adjacent an end of the conduit. The drain hole is formed at an angle relative to a plane made perpendicular to a center axis of said conduit. An air machine, an air machine assembly and a method are also disclosed.

Abstract: A fan unit assembly includes a fan rack, fan units and handles. The fan rack includes a carrier and parallel partition boards erected on the carrier to define fan-disposing regions. The partition board has at least one first positioning part and at least one first guiding part facing the corresponding fan-disposing region. The fan unit has two side surfaces and a front surface. The front surface connects the side surfaces. The side surfaces respectively have a second guiding part engaged with the first guiding part. The fan unit is suitable to move along the first guiding part through the second guiding part. The handles are disposed at the front surface and both ends thereof are bent to form two pivot portions respectively pivoted on the side surfaces. Each pivot portion has a second positioning part. When the handle rotates towards the front surface, the positioning parts interfere with each other.

Abstract: A housing for a wind turbine includes a plurality of spine members with a central rib and opposed channels. Frame members are attached to adjacent spine members. The housing includes divergent frame members having a pair of longitudinal members which are inserted into channels of a spine member. The housing includes central support members, each central support member is attached to a divergent frame member. Each of the central support members is attached near the center of one of the divergent frame members. The housing also includes outer plates, each outer plate attached to and between adjacent spine members. Channels face in the opposite direction from adjacent channels on the spines. An inner shroud is attached to the spine members. Air passages are created underneath the arcuate outer plates. A cowling is attached to the end plates.

Abstract: A turbine housing of an exhaust gas turbocharger includes an outer housing, in which an inner housing with a tubular nozzle and an outlet duct for connection to an exhaust gas system is arranged, wherein the outlet duct is coupled to the tubular nozzle via a sealing lip for relative movement. The sealing lip is inwardly evertedly pushed onto the nozzle and for positional fixing, a sliding sleeve is further arranged on the nozzle, wherein the sliding sleeve and the nozzle form a gap in which an end of the sealing lip is received. This avoids that the sealing lip lifts of due to pressure differences and thus that gas leaks occur. Further, an end of the sealing lip is arranged so as to be thermally protected.