Abstract: The invention provides a fixation device for a turbine, including a flange mounted on a housing of the turbine and a nut assembly received in the flange to apply fixation to an component inside the housing. The flange is fixed to the housing by a plurality of first bolts and comprises a central threaded hole. The nut assembly comprises a nut body with a first hole formed along the central axis of the nut body and a plurality of second holes formed around the central axis, and a plurality of second bolts received in the respective second holes. The nut body is formed with thread on its outer circumferential surface and fitted within the central threaded hole of the flange. The second bolts are screwed in the second holes to apply fixation against the component inside the housing of the turbine. The nut assembly further comprises a plurality of sleeves received in the respective second holes, and the plurality of second bolts are received in the respective sleeves.

Abstract: A ventilation fan with illumination includes a housing, a fan, and lighting equipment in the housing. The housing includes a first opening connected to an air outlet, the first opening communicating with a duct, and a second opening that communicates with an interior space, The lighting equipment includes a light, a cover in the housing that surrounds the light periphery, the cover reflecting light and transmitting the light into the space through the second opening, and a restrictor that restricts passage of air between the light periphery and the lighting cover. An air intake gap is provided between a lower end of the cover and an edge of the second opening and introduced through the second opening and the air intake gap, is discharged through the first opening into the duct, the edge of the second opening being located below the lower end of the cover.

Abstract: The invention relates to a nacelle for a turbojet, of the type comprising a downstream structure having an outer structure (6) that defines, together with an inner concentric structure (9) for surrounding the downstream portion of the turbojet, an annular flow channel (8), characterised in that a portion at least of said inner structure (9) is mounted so as to be capable of a translation movement along the longitudinal axis of the nacelle so that it can move between a working position, in which the inner structure acts as a casing for the downstream portion of the turbojet, and a maintenance position in which the inner structure exposes said downstream portion of the turbojet.

Abstract: A mounting apparatus includes a bracket and two shafts. The bracket includes a fixing plate defining a number of horizontally arranged vents, for mounting a number of fans to the rear side of the fixing plate, with each vent aligning with one of the fans. The shafts are respectively and horizontally mounted to a top and a middle of a front side of the bracket. A number of shield plates are rotatably connected to the shafts. The shield plates hang vertically under the corresponding shafts by gravity. Each of the vents is covered by two vertically aligned shield plates upon a condition that the gravity of the two shield plates are not overcome by airflows passing through the vents.

Abstract: A fan cooling system has individual fan modules which are connected together in an end-to-end configuration, where one of the fan modules is connected to a mechanism which rotates the linear array of fan modules. The fan modules are substantially identical, which allows prefabrication of the fan modules prior to on-site installation of the system. Each fan module may contain water injection piping and nozzles, which allows the fan cooling system to dispense fog. The linear array of fan modules may be rotated along a longitudinal axis, such that the axial flow direction of the fans may be changed with respect to a vertical plane. A suggested use of the fan cooling system is for the cooling of livestock in large livestock structures.

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: A turbocharger has a rotor housing. Said rotor housing has an insertion element. Said insertion element is configured such that the same forms an over-hanging spiral together with said rotor housing.

Abstract: A combining assembly for a fan fixing base is fixed in a housing and includes a fan module and a frame plate. The fan module includes a fixing base, a heat-dissipating fan disposed in the fixing base, and a plurality of locking elements. The heat-dissipating fan is provided with a plurality of locking holes. The fixing base has a plurality of through-holes. The locking elements are disposed through the through-holes to be connected into the locking holes, thereby fixing the heat-dissipating fan into the fixing base. The frame plate is provided with a plurality of positioning troughs to correspond to the locking elements. The fan module is engaged in the positioning troughs via the locking elements.

Abstract: A fan assembly used in an electronic device is disclosed. The fan assembly includes a fan and the casing securing the fan. The casing includes a top plate, a front plate, a rear plate and two side plates. The top plate comprises a plurality of mounting pieces and a mounting portion located on each mounting piece. The front plate is secured to the fan. The rear plate is secured to the fan and opposite to the front plate. The two side plates are secured to the front plate and the rear plate. Each side plate comprises two positioning pieces, and each positioning piece defines a positioning hole. The plurality of mounting pieces abuts the two positioning pieces of the two side plates, and the mounting piece is engaged in the positioning hole.

Abstract: A mounting device for mounting a fan includes a base board and two fixing assemblies. The fan includes two opposite boards. The base board forms four rods. Each fixing assembly includes a receiving member and an engaging member. The receiving member includes a first pole capable of extending through a corresponding one of the boards and a first block abutting against an outer surface of the board. The engaging member includes a second pole capable of extending though the other one of the boards to be engaged in the first pole, and a second block abutting against an outer surface of the other board. Each of the first and second blocks defines a fixing hole through which a corresponding one of the rods is capable of extending.

Abstract: A mounting device for mounting a number of fans includes a rack and a number of fixing members. The rack includes a bottom wall and two sidewalls perpendicularly extending up from opposite sides of the rack. Each sidewall defines a number of vents spaced along the lengthwise of the sidewall. Each fixing member includes a board perpendicularly mounted to the bottom wall and positioned at a side of two aligning vents, and a blocking member mounted to the board and slidable along the lengthwise of the sidewalls to block a top of a fan.

Abstract: A method for handling wind turbine sub-assemblies (14, 16) includes coupling a connecting device (44) to a connector (46) of a hoisting device at a first connection interface of the connecting device; coupling a first wind turbine sub-assembly to the connecting device at a second connection interface (60) of the connecting device; moving the first wind turbine sub-assembly with the hoisting device; coupling a second wind turbine sub-assembly different than the first wind turbine sub-assembly to the connection device at a third connection interface (76) of the connecting device; and moving the second wind turbine sub-assembly with the hoisting device. An apparatus (26) for handling wind turbine sub-assemblies is also disclosed.

Abstract: The axial fan has a motor (1), on the rotor side of which an impeller is fixed, wherein fan blades (24) with a front and a rear edge (26, 27) project from the hub of said impeller. The motor (1) is fixed to a housing (3) by means of a suspension (2). The suspension has a bracing part (4 to 8) made of a flat material, said bracing part connecting the motor (1) to the housing (3) and being arranged in an approximately vertical manner in the flow direction of the air. The aim of the invention is to design the axial fan such that the axial fan has a high overall efficiency and only a low flow resistance. This is achieved in that the bracing part (4 to 8) is provided with at least one recess (7) over a part of the length of the bracing part. The flow resistance due to the bracing part is minimized by means of the recess. The recess reduces the weight of the axial fan.

Abstract: A fan cover (10), on which a fan motor (11) is mounted, includes: a fan cover flat portion in which an opening portion (12) is formed; a protruding portion (13) extending from the fan cover flat portion around the opening portion; and a supporting portion (14), which is arranged on the protruding portion, for supporting the fan motor, wherein a distance between the fan cover flat portion and the supporting portion of the protruding portion is smaller than the thickness of the fan motor.

Abstract: A fan assembly includes a first fan and a second fan stacked together. Each of the first fan and the second fan includes a frame and a supporting base received in the frame. Several extending portions extend from a bottom of the frame of the first fan. A buckling block is formed on an inner side face of each of the extending portions. Several receiving portions are formed at a top of the frame of the second fan corresponding to the extending portions, respectively. A positioning groove is defined in each of the receiving portions. The buckling blocks are engagingly received in the positioning grooves.

Abstract: A device for supporting a ring of a gas turbine, the ring configured to surround mobile blades of the turbine which are driven by a gas stream flowing upstream to downstream. The device includes at least one upstream hook facing upstream, to be housed in an upstream groove of the ring, opened toward the downstream direction, and at least one downstream hook facing downstream, to be housed in a downstream groove of the ring, opened toward the upstream direction. The hooks are protected and clearances at apexes of the blades are more easily controlled. The device further includes, upstream from the upstream hook, a mechanism injecting cooling gas to cool the upstream hook and/or includes, downstream from the downstream hook, a mechanism injecting a cooling gas to cool the downstream hook.

Abstract: An exhaust turbocharger (1) having a turbine housing (2), which has an inlet stub (3), and having a connecting device (4) for securing the inlet stub (3) on an exhaust-gas supply device (5). The connecting device (4) is designed as a plug-in connecting device.

Abstract: An exemplary turbomachine securing apparatus includes a coupling member that couples a first component to a second component within a turbomachine. The first component and the second component are both non-rotating components during operation of the turbomachine. The coupling member limiting relative circumferential movement between the first component and the second component, and permitting relative radial movement.

Abstract: A nacelle includes an outer structure provided with a thrust reverser and a front frame, a movable cowl, and an inner structure covering a downstream section of a turbojet engine. The outer structure and the inner structure define a flow stream of an air flow. In particular, the connection of the front frame and diversion cascade of the thrust reverser which is mounted on a reduced transverse section area of the movable cowl is centered on an axis offset relative to an axis on which the connection of the front frame and the diversion cascade mounted on the remainder of the periphery of the movable cowl is centered.

Abstract: A fan assembly includes a fan, a bracket, and a shield. The fan includes a first securing plate, which defines a plurality of first locking holes. The bracket includes a mounting plate, which defines a plurality of vent holes. A first group of locking members is mounted on the mounting plate. The mounting plate includes a pair of restricting pieces. The shield is restricted between the pair of restricting pieces to be mounted on one side of the mounting plate. The first group of locking members is mounted in the plurality of first locking holes to mount the fan on another side of the mounting plate, and the plurality of vent holes is configured to communicate the fan with the shield.

Abstract: A support bar for a steam turbine nozzle assembly is disclosed. In one embodiment, the support bar includes a hook-shaped portion for engaging a lip portion of a steam turbine diaphragm, wherein the steam turbine support bar is configured to non-affixedly join a steam turbine casing to the steam turbine diaphragm.

Abstract: A turbine shroud apparatus for a gas turbine engine includes: a plurality of arcuate shroud segments arranged as an annular shroud, each of the shroud segments comprising low-ductility material 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 an open channel is formed through the outer wall of each shroud segment; an annular stationary structure surrounding the shroud segments; and a hanger received in the open channel of each shroud segment and mechanically coupled to the stationary structure, each of the hangers passing through the respective open channel and including an enlarged portion having greater cross-sectional area than the open channel, the enlarged portion engaging the outer wall of the respective shroud segment, so as to retain the shroud segment radially relative to the stationary structure.

Abstract: A fan includes a casing having an air inlet and an air outlet, an impeller housing located within the casing, an impeller located within the impeller housing for generating an air flow along a path extending from the air inlet to the air outlet through the impeller housing, a motor housing connected to the impeller housing, and a motor located within the motor housing for driving the impeller. A bellows support is provided for mounting the impeller housing within the casing. The bellows support is disposed on a seat connected to the casing. The bellows support extends about the impeller housing and forms a seal between the impeller housing and the casing.

Abstract: A connection arm couples to a cooling fan main body to enclose wires extending from the main body to an end of the connection arm that holds a plug of the wires in a position aligned with a circuit board cooling fan socket. Wires enclosed in the connection arm slip through a slot along the side of the connection arm and are protected from view by a cable cover disposed along the top surface of the cooling fan and connection arm.

Abstract: A method is provided for adjusting a position of a blade ring relative to a rotor in a gas turbine engine. An outer casing surrounds the blade ring and the blade ring surrounds the rotor. The method comprises: determining an amount of vertical movement needed to reposition the blade ring relative to the rotor so that the blade ring is at a desired position relative to the rotor; providing at least one torque pin assembly comprising a torque pin and a variable thickness defining structure; determining a change in the thickness of the variable thickness defining structure so as to effect the necessary vertical movement of the blade ring; changing the thickness of the variable thickness defining structure; and coupling the at least one torque pin assembly to the outer casing such that at least one torque pin engages the blade ring. A gas turbine engine is provided having structure for adjusting a position of a blade ring relative to a rotor.

Abstract: A fan module includes a bracket, a mounting plate, and a fan fixed to the mounting plate. A first side of the mounting plate is pivotably attached to the bracket. A second side of the mounting plate can be fixed to different positions on the bracket.

Abstract: A fan assembly includes a case, a bracket and a fan module. The cage includes a ventilation plate. An installation portion and a positioning post are located on the ventilation plate. The fan module is secured to the ventilation plate and includes a bracket and a fan secured to the bracket. The bracket includes a body, a first sidewall, and a second sidewall. The first and second sidewalls are located on opposite sides of the body. The first sidewall defines a first receiving slot and a first positioning hole. The second sidewall defines a second receiving slot and a second positioning hole. The first positioning hole is aligned with the second positioning hole. An area of the first receiving slot is larger than that of the second receiving slot. The positioning post is engaged in the positioning hole. The installation portion is received in the first receiving slot.

Abstract: A mounting device for fixing fans comprises a bottom plate and a top plate. The fans are set between the bottom plate and the top plate. The bottom plate forms a number of rods. The fan comprises two opposite boards. A number of fixing assemblies are arranged on the boards. Each fixing assembly defines a number of fixing holes for receiving corresponding rods. A number of springs are arranged between the bottom plate and the fixing assemblies.

Abstract: A device for supporting and securing a piece of equipment on an aircraft engine or nacelle case, including a vibration damper including a first part secured to the case and a second coaxial part rigidly connected to the piece of equipment, the damper associated with a safety member configured to hold the damper in place on the case in the event of damper failure or breakage. The safety member, which is independent of the damper, is mounted astride the damper and secured to the case.

Abstract: A device for repairing a casing holder of an aeronautical engine extending radially relative to the engine rotational axis and including a plurality of lips, each having a hole drilled therein and evenly distributed on the circumference of the holder. The device includes at least one reinforcement holder that can be attached to clean lips of the case holder via through-holes or blind-holes, the reinforcement holder having two orthogonal planes of symmetry. The device further includes a reconditioning holder mounted on the reinforcement holder via a first part using attachment means positioned in one of the planes of symmetry of the reinforcement holder.

Abstract: An alignment assembly for mounting and aligning an inner shell within an outer shell is disclosed. The alignment assembly generally includes a first bushing and a second bushing configured to be received within at least one of an arm extending radially between the inner and outer shells and a boss of the outer shell. The first bushing may generally have an eccentric configuration and the second bushing may include an eccentric portion extending within the first bushing. Additionally, the alignment assembly may include a connection member extending within at least one of said first bushing and said second bushing.

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: In certain embodiments of the present disclosure, a turbine casing assembly is described. The turbine casing assembly includes an inner casing and an outer casing surrounding the inner casing. The outer casing has a first outer casing section and a second outer casing section that join together along a flange. A bolt extends through the flange and joins together the first outer casing section and the second outer casing section. The turbine casing assembly further includes a pin. The pin has a segment defining an opening therethrough. The pin extends through the inner casing and the outer casing and supports the inner casing relative to the outer casing. The bolt passes through the opening defined by the pin.

Abstract: An electronic device includes an air dam module. The air dam module includes a frame defining a vent, a first rotating member, a second rotating member, and two third rotating members. The first rotating member is rotatably connected to a surface bounding the vent, to vertically block a lower half of the vent by its gravity. The second rotating member is rotatably connected to the surface bounding the vent. The third rotating members are rotatably connected to opposite ends of the second rotating member. The second and third rotating members vertically block an upper half of the vent by their gravities.

Abstract: A seal segment is provided for a shroud ring of a rotor of a gas turbine engine. The seal segment is positioned, in use, radially adjacent the rotor. The seal segment has two or more spaced passageways. In use, a respective support bar can be contained within each passageway. The support bars allow attachment of the seal segment to the engine casing. Each passageway has an elliptical or substantially elliptical cross-section with a minor diameter and a major diameter, the minor diameter being substantially aligned with the radial direction. The respective support bar has a correspondingly elliptical or substantially elliptical cross-section for a close fit in the passageway.

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 boss for attachment of an auxiliary device to a fan case of an engine is comprised of a pedestal including a plurality of accumulated layers of reinforcement fibers and a matrix combining the reinforcement fibers together, the pedestal comprising a bottom face in a shape capable of being in close contact with an outer periphery of the fan case; and an embedded body embedded in the pedestal and including a combining structure combinable with the auxiliary device.

Abstract: A mechanical system for a turbomachine includes a turbomachine part to be attached and a plurality of threaded attachment elements mounted on the turbomachine part in sequence along a line. The attachment elements fix the turbomachine part to the turbomachine. At least some of the attachment elements are arranged to be prevented from rotating by mutual cooperation about their corresponding thread axes, by a rotation prevention system provided on each of these attachment elements called self-locking elements. The self-locked elements cooperate in pairs, each pair including two directly consecutive self-locked elements along the line. At least one of the pairs has a distance between the thread axes of its two self-locked elements less than the distance between one of these two thread axes and the axis of either of the two attachment elements arranged along the line on each side of the at least one of the pairs.

Abstract: A system includes a turbomachine platform including a first docking guide. The turbomachine platform supports a turbomachine skid, and the skid includes a second docking guide. The first docking guide is configured to interface with the second docking guide in order to guide the turbomachine skid between a docked position and an undocked position relative to other equipment supported by the platform.

Abstract: A turbine assembly mounted to a pump rotor via mounting bolts. The turbine includes fins extending therefrom for pumping gasses and suspended particles from a semiconductor processing chamber. The tops of the bolts are recessed from the top surface of the turbine in a bolt cavity having an open end. A cap member is mounted over and seals the open end of the bolt cavity via a center bolt. The cap member has a shaped upper surface (conical, parabolic, squared, rounded) for deflecting particles away from the center of the turbine and toward the turbine's fins. The cap member's upper surface can include particle deflecting features such as fins, channels or asymmetric shapes to enhance particle deflection as the cap member rotates. The cap member can include a compressible o-ring for a friction fit mounting to the turbine.

Abstract: A gas turbine engine includes a compressor assembly that is rotationally coupled to a shaft. The engine includes a radial diffuser assembly coupled to a shroud of the compressor assembly and positioned to receive compressed air from a centrifugal impeller. The radial diffuser assembly includes a first arcuate wall and a second wall, and a near axial diffuser coupled to the radial diffuser assembly and positioned to receive the compressed air from the radial diffuser assembly. The gas turbine includes a gas seal coupled between the second wall and a wall of the near axial diffuser, the gas seal configured to prevent the compressed air from passing through the seal while allowing relative motion between the radial diffuser assembly and the near axial diffuser.

Abstract: A push-lock pin for connecting a tile to a gas turbine engine wall according to an exemplary aspect of the present disclosure includes, among other things, a housing extending longitudinally along an axis; a shaft assembly within the housing, the shaft assembly including a push-down pop-up mechanism and a locking mechanism, the locking mechanism moveable to a locked position such that the locking mechanism limits movement of a tile away from a gas turbine engine wall; and a stop feature to limit movement of the tile toward the gas turbine engine wall.

Abstract: In a turbine housing for an exhaust gas turbocharger of an internal combustion engine with at least one spiral channel, which can be coupled into an exhaust gas flow of an exhaust tract of the internal combustion engine, and a receiving space for a turbine wheel which is disposed downstream of the at least one spiral channel and can be acted upon by the exhaust gas of the internal combustion engine passing through the at least one spiral channel of the turbine housing, there is at least one partial housing including the at least one spiral channel, and a housing module which is fastened to the partial housing and has a vane structure disposed upstream of the receiving space which also includes an attachment surface for a bearing section of the exhaust gas turbocharger. The invention also resides in an exhaust gas turbocharger with such a turbine housing as well as to a method for producing such a turbine housing.

Abstract: In a connection assembly of a turbine housing to a bearing housing of an exhaust gas turbocharger and to an exhaust gas turbocharger, wherein the turbine housing and the bearing housing are centered relative to each other and connected to each other in the region of a connection joint including a sealing assembly with a heat shield disposed between the turbine housing and the bearing housing, at least one cutout is provided in the heat shield for accommodating a centering means by way of which the turbine housing and the bearing housing are directly centered relative to one another.

Abstract: A support system for a dynamoelectric machine is disclosed. In one embodiment, the support system includes: a mounting pad having a first face and a second face, the second face including a pair of slots; a pair of spring bars welded or brazed to the mounting pad at the pair of slots; a collar welded or brazed to the first face of the mounting pad; and a key bar between and affixed to the pair of spring bars.

Abstract: A first ceramic matrix composite structure having a first flange with a first aperture, and a second structure having a second flange with a second aperture are clamped together by a fastener and spring assembly. The second flange is in contact with the first flange and the apertures of the first and second flanges align with each other. A threaded fastener having a thermal expansion rate that is different than the thermal expansion rate of at least one of the first ceramic matrix composite structure and second structure extends through the aligned apertures. The fastener includes a bolt, a nut, and a spring assembly that maintains a constant clamping pressure irrespective of the thermal expansion differences between the bolt and the first ceramic matrix composite structure and second structure.

Abstract: A support arrangement is provided for an inner casing of a turbine having an inner casing with upper and lower sections secured together along a first interface lying substantially in a horizontal plane containing a longitudinal centerline of a turbine rotor. An outer shell substantially encloses the inner casing, and in the inner casing is supported directly on an external foundation at a mounting location below the longitudinal centerline.

Abstract: A positioning tool includes an actuating member and a rotating member rotatably attached to the actuating member. The actuating member includes a supporting lump. Two positioning pins are located on the supporting lump. The rotating member includes a rotating plate located between the two positioning pins. Three latching pins are located on the rotating plate.

Abstract: The invention refers to a rotary flow machine having a rotor unit, rotating about a rotational axis, around which in at least one partial axial area a stationary inner housing (IH) is provided at a radial distance. The stationary inner housing (IH) can be divided up along the rotational axis in an upper and a lower inner housing half which adjoin each other along a horizontal split plane. The inner housing (IH) is surrounded in at least one axial section by an outer housing (OH) which can be divided up along the rotational axis in one upper and one lower outer housing half. Further a method for disassembling of a rotary flow machine is disclosed. The lower inner housing half provides support means which support the inner lower housing half on the lower outer housing half. The support means are detachably mounted at the lower inner housing half at least at two opposite support positions (P1, P2) relative to the rotational axis along the split plane.

Abstract: A fan securing device includes first and second holders. The first holder includes a first holding frame that has two holding slots located in opposite sides of the first holding frame, and two first locking units respectively formed adjacent to the holding slots. The second holder includes a second holding frame that has two connecting arms located on opposite sides of the second holding frame and extending respectively into the holding slots. Each connecting arm has a plurality of second locking units. Each first locking unit engages a selected one of the second locking units of a respective one of the connecting arms so as to clamp at least one cooling fan between the first and second surfaces.