Abstract: An example exit guide vane for a gas turbine engine is mounted adjacent to a diffuser case defining an air flow path. A thrust balance seal is attached to the diffuser and the exit guide vane is mounted adjacent the diffuser case for guiding air flow into the air flow path. The exit guide vane is mounted adjacent to the diffuser without interfering with the air flow path or restricting thermal expansion.

Abstract: A method of assembling a turbomachine that includes a rotor and a stationary component is provided. The method includes coupling a housing to the stationary component using at least one biasing member, wherein the housing extending circumferentially about the rotor. The method also includes coupling at least one annular ring to the housing, and coupling a plurality of plate members to the housing such that the at least one annular ring extends from the housing towards the rotor and partially through the plurality of plate members.

Abstract: A seal for restricting leakage of a fluid through a gap disposed between rotating and stationary components concentrically aligned within a gas turbine engine comprises a sealing member and a land. The sealing member is positioned on either the rotating or stationary component of the gas turbine engine and closes a gap between the rotating member and the stationary member. The land is positioned opposite the sealing member on either the rotating or stationary component of the gas turbine engine such that a clearance height is provided between the sealing member and the land. In one embodiment, the land is geometrically shaped according to expected changes in the gap and relative axial position of the sealing member and land during operation of the gas turbine engine. The sealing member and the land are positioned with respect to each other so that the clearance height is maintained approximately constant during operation of the gas turbine engine.

Abstract: The air seal arrangement is for a disc wheel in a gas turbine engine. The disc wheel comprises a sleeve portion having an outer surface. The arrangement comprises a static knife edge seal in registry with the outer surface. The static knife edge seal has a free end adjacent to the outer surface.

Abstract: There is provided a centrifugal turbo machine comprising: a volute casing; a rotation axis coupled with the volute casing through a bearing; an impeller which is coupled to an end of the rotation axis and sucks fluid with a centrifugal force due to its rotation; and an axial thrust control member which is coupled to the volute casing at the rear of the impeller in a direction in which the fluid flows and prevents rotation of the fluid by the impeller. It is easy to fabricate and install the centrifugal turbo machine and it is possible to reduce the difference in static pressure of fluid by using the economical axial thrust control member so as to prevent the generation of the axial thrust, which results in damage of the bearing, etc. Therefore, it is possible to stably operate the centrifugal turbo machine.

Abstract: A gas turbine engine includes a high-pressure compressor having an impeller and an impeller baffle having a generally annular body, the impeller baffle spaced apart from a back face of an impeller to create an airspace therebetween, the airspace communicating between an impeller exit and an apparatus to be pressurized, the impeller baffle including a plurality of generally radially-disposed ribs extending into the airspace for diminishing the velocity of air swirling in the airspace.

Abstract: The rim seal is positioned in an annular space between blades and a non-rotating adjacent structure in a gas turbine engine. The rim seal is connectable to the non-rotating structure and is made of an abradable material.

Abstract: A method of manufacturing a gas turbine engine includes providing a turbine mid-frame, coupling a plurality of rotor blades to a rotor disk, the rotor disk is coupled axially aft from the turbine mid-frame such that a cavity is defined between the rotor disk and the turbine mid-frame, and forming at least one opening extending through the turbine mid-frame to facilitate channeling cooling air into the gap, the opening configured to impart a high relative tangential velocity into the cooling air discharged from the opening.

Abstract: An axial flow compressor is provided with a rotor blade row (10) which is formed such that an outlet cross sectional area is larger than an inlet cross sectional area so as to reduce a speed in an axial direction and reduce a pressure difference between a positive pressure surface and a negative pressure surface. Further, a stator blade row (11) is provided in a downstream side of the rotor blade row (10). An output cross sectional area of the stator blade row (11) is structured such as to be smaller than an inlet cross sectional area of the rotor blade row (10).

Abstract: A singlet welded nozzle hybrid design that includes a singlet, that is, a single airfoil with respective inner and outer sidewall components. The outer sidewall component is received in a radial and circumferential groove of an outer carrier. The connection of the inner sidewall can be achieved by mechanically fitting and welded the inner sidewalls to either a seal carrier or a small ring, or a small radial weld may be provided between the sidewall endfaces of circumferentially adjacent singlets.

Abstract: A method of making a pump (10) including a polymeric pump housing (12) and a drive shaft (14) mounted for rotation in a bearing (16), the bearing (16) having on an exterior surface at least one engagement formation (44),—the method including the step of moulding the pump housing (12) around the bearing (16) such that the housing (12) co-operates with the engagement formation (44) to restrict movement of the bearing (16) with respect to the housing (12).

Abstract: A fan assembly includes an end bracket which is coupled to a motor assembly. The end bracket includes a circumferential channel which is interrupted by an opening. A fan is provided which includes a plurality of blades. A shroud at least partially encloses the fan and defines a chamber. An insert, which may or may not be an integral part of the end bracket, is received in the chamber and includes a circumferential ramp. The circumferential ramp is configured to provide the chamber with an internal cross-sectional area which varies circumferentially so as to improve airflow efficiency.

Abstract: A turbomachine has, on its inner casing (5) and on its shaft, recesses into which shrouds of rotor blades and/or of guide vanes (2a) protrude. The recesses are configured with wave-shaped contouring arrangements (10), which extend over their periphery. The contouring (10) extends over axially extending regions of the recess and consists of periodic elevations and depressions (14, 15) in the radial direction. They can also be effected on the radially extending regions of the recess and on the shrouds. The undulation-shaped contouring arrangements are used to counteract existing pressure fields and to reduce performance losses due to mixing processes between the leakage flow and the main flow.

Abstract: A system includes a case, a stator, a ring seal, and a rotor and is configured to pump air out of a housing. The case is mounted on the housing. The stator is mounted within the case and has two sides, an inner diameter and an outer diameter, where the first side faces the case. The ring seal is disposed between the stator first side and the case. The rotor is mounted on a shaft and has a side facing the stator first side. The rotor side has grooves, an inner and outer peripheral surfaces, and is configured to pump air from the outer peripheral surface to the inner peripheral surface to thereby pump air out of the housing. The stator inner diameter is configured and the ring seal is positioned such that separation forces are substantially equal to or less than closing forces during a system breach.

Abstract: A compressor for a turbine engine includes multiple compressor disks having rotor blades mounted about the circumference of each of the disks. A plurality of stator vanes extend between the rotor blades of axially adjacent disks. A knife edge seal segment is supported by each disk backbone extending from the disks and contacts the stator vanes to restrict leakage of compressed air from between the stator vane and the compressor rotor to limit the recirculation of air. Retaining flanges extend from each disk rim to retain the knife edge seal segments to the disk backbone and spacer bridges integral to the knife edge seal segments prevent axial movement of the knife edge seal segments. A plurality of lock assemblies are spaced about the circumference of the disk backbone to prevent circumferential shifting and rotating of the knife edge seal segments during operation.

Abstract: A fastener for a turbine engine includes a bolt and a ceramic matrix composite (CMC) cap mechanically secured to the bolt. CMC components are attached to an exhaust nozzle case with the fasteners. The fastener includes a bolt made of metal and having a head. A CMC cap is located on the head of the bolt and secured to the bolt by a mechanical device. The mechanical device allows the CMC cap to have a different thermal expansion than the bolt. The CMC cap also acts as a thermal shield for the bolt, aiding in the reduction of a heat signature of the turbine engine.

Abstract: A seal device 25B has a wear-ring 31 fixed to a casing 2 of a centrifugal pump and a floating ring 32. An annular gap 36 between an inner peripheral surface of a through bore 32a formed in the floating ring 32 and an outer peripheral surface of a mouth ring portion 19 of an impeller 5B is smaller than an annular gap 35 between an inner peripheral surface of a through bore 31a formed in the wear-ring 31 and the outer peripheral surface of the mouth ring portion 19. Fluid leakage from a high pressure area to a low pressure area in the casing 2 through the gaps is prevented.

Abstract: This invention refers to a labyrinth seal for a gas turbine engine incorporating from upstream to downstream ends, a high pressure compressor with a rotor, a diffuser and a fixed wall element forming at least one part of the internal envelope of the combustion chamber said seal comprising a stator part mounted on the wall element by virtue of an attaching part with flanges and supporting an annular wearing part said wearing part working jointly with a rotor element provided with at least one circumferential tooth integral with rotor of the compressor to form the labyrinth seal. It is characterized by the fact that at least one of the flanges of said attaching means is heavy enough to harmonize the rate of dilatation of the stator part with respect to the dilatation rate of the rotor element during engine accelerations. In conformity with another characteristic, ventilation orifices are arranged in the wall element.

Abstract: A flow machine for a fluid is presented with a radial sealing gap (9) between stator parts (4) and a rotor (3), wherein at least one wear ring (5) is provided at the sealing gap and is fastened to a stator part (4) via an elastically deformable fastening part. The fastening part (6) is connected on the one side to the stator part (4). On this side a radial gap (8) is formed between an outer jacket surface of the wear ring and the fastening part and, on the other side, with the wear ring. On this side a radial gap (7) is formed between an outer jacket surface of the fastening part and the stator part.

Abstract: A ring seal is mounted in the annular gap between a shroud platform overhanging portion and the surrounding shroud support to minimize cooling air leakage through the shroud.

Abstract: A centrifugal compressor is disclosed as including a case, a compressor chamber, and an impeller in the compressor chamber for compressing fluid from an inlet opening and forcing compressed fluid through an outlet opening. Moreover, the compressor includes an insert rotatably supported on the case. The insert is adjacent the impeller and serves to minimize catastrophic compressor failure that might otherwise occur as a result of contact between the impeller and compressor chamber wall.

Abstract: A shroud segment for being incorporated in a gas turbine engine so as to suppress influence of hot combustion gas on a turbine case of the gas turbine engine is provided with a back plate having first and second plate portions formed in an arc shape and supported by the turbine case, a touching member integrally formed on an inner surface of the back plate for touching with a rotating turbine blade, a pair of first seal slots for receiving a pair of first spline seal plate, a pair of second seal slots for receiving a pair of second spline seal plate and a pair of seal gaps respectively communicating with the first seal slots and the second seal slots. The seal gaps are respectively provided with abutment surfaces recessed from front surfaces of the second seal slots so as to receive front ends of the first spline seal plates.

Abstract: A method facilitates assembling a variable vane assembly for a gas turbine engine including a casing and an inner shroud. The method comprises providing at least one variable vane including a radially inner spindle that includes a groove defined therein that has at least one machined face, and coupling the variable vane radially between the casing and the inner shroud such that at least a portion of the radially inner spindle is inserted at least partially through an opening extending radially through the inner shroud. The method also comprises securing the variable vane to the inner shroud by engaging the spindle machined face with a retainer coupled to the inner shroud.

Abstract: An aircraft turbojet including a fan having a hub driven by a shaft carried by at least one bearing connected to the structure of the turbojet by a bearing support that includes an interposed decoupling device. The hub carries at its periphery a plurality of blades that move inside a retention casing with radial clearance E between the tips of the blades and an inside wall of the retention casing. The inside wall is lined in a layer of abradable material suitable for being planed away by the tips of the rotating blades. The tips of the blades are suitable for being disintegrated by the inside wall of the retention casing in the event of an impact following the appearance of unbalance that has led to the bearing being decoupled, to obtain a clearance J>E as required for operation of the decoupler.

Abstract: To further isolate imbalances in a rotating structure such as a gas turbine engine, an effective length between two bearings may exceed an actual length. This may be achieved via one or more tapering bearing supports associated with at least one of the bearings.

Abstract: A fastener shield for use in a fluid flow path within a gas turbine engine for reducing fluid drag and heating generated by fluid flow over a plurality of circumferentially spaced bolts. The fastener shield has a radially-extending, downstream-facing mounting flange with a plurality of circumferentially spaced bolt holes positioned to receive respective engine mounting bolts therethrough and to attach the mounting flange to elements of the turbine engine. A curved, upstream-facing fastener shield cover is positioned in spaced-apart relation to the mounting flange for at least partially covering and separating an exposed, upstream-facing portion of the bolts from the fluid flow to thereby reduce drag and consequent heating of the bolts. A plurality of closely spaced-apart, spirally-oriented channels are formed in the fastener shield cover for deflecting the fluid flow impinging on the fastener shield cover, thereby increasing the tangential velocity and lowering the relative temperature of the fluid flow.

Abstract: An intelligent seal support management system includes a device for automatically compensating for increased heat or decreased heat in a vessel.

Abstract: A fan seat (30, 30?) includes a basis (31) with a vertical extending tubal portion (32) having a pair of flanges (33) integrally formed on opposite ends of an inner circumferential surface thereof, and a bearing set (34, 34?) located in the tubal portion and sandwiched between the flanges. The bearing set includes a tube (36) and a pair of bearings (38) firmly secured in opposite ends of the tube. A method for producing the fan seat includes the following steps: providing a mold (50) with a cavity (53), locating the bearing set in the cavity with a space (60) formed between the bearing set and the mold corresponding to the tubal portion, injecting molten material into the space, and cooling the molten material whereby the molten material congeals into the tubal portion and integrates with the tube.

Abstract: A gas friction pump, comprising stationary pump-active components (14) and rotatable pump-active components (15) secured on a rotatable rotor shaft (4), wherein the rotor shaft is supported with a bearing (5) at the high-vacuum-side end and a bearing arrangement at a fore-vacuum side end, characterized in that the high-vacuum side bearing is formed as a conventional bearing, and the fore-vacuum bearing arrangement contains at least one gas bearing. In an advantageous embodiment, the gas bearing is formed as a module and can be brought in engagement with a cylindrical portion of the housing and secured therein.

Abstract: A stationary gas turbine engine includes an axial compressor; a turbine; a stationary inner barrel downstream of the compressor; a brush seal including a ring-shaped holder supported by the inner barrel, and a multiplicity of inwardly extending bristle members having an ambient temperature clearance of not less than 0.015 percent of a rotor land region diameter of the rotor under cold conditions for restricting air passage into the chamber from the compressor. The flow of cooling air from the chamber is preferably alterable by a fluid port extending through one wall of the inner barrel, the fluid port being connected to an auxiliary source of pressure air external of the inner barrel, whereby pressure air from the auxiliary source augments the flow of cooling air from the chamber. A calibrated needle valve can adjustably restrict the flow of auxiliary air for controlling a monitored operating parameter such as the temperature within the chamber.

Abstract: A compressor impeller for use with a boreless turbocharger is provided in accordance with this invention. The compressor impeller comprises an integral hub projecting axially therefrom that includes a partial bore therein that extends from an open to a close bore end. The bore includes a threaded portion that is configured to accommodate threaded engagement with an end of a common shaft disposed through a turbocharger housing and attached at an opposite end to a turbine wheel. The hub is specially configured so that the threaded portion has a relatively increased wall thickness when compared to a remaining portion of the bore disposed between the threaded portion and the end of the bore. The bore is configured providing a section having a reduced wall thickness, between the threaded portion and the bore closed end, for purposes of providing a preferential stress relief mechanism.

Abstract: Spline seals are provided in registering end faces of upper and lower diaphragm segments in a steam turbine at each of the horizontal joints. The diaphragm segments each include inner and outer semi-annular rings with circumferentially spaced partitions extending therebetween. The registering end faces of each of the inner and outer semi-annular rings of the segments are spanned by spline seals which may comprise a sheet metal plate, a sheet metal body having reversely-curved ends, a solid body having bulbous ends or a sheet metal plate covered by a metallic or ceramic woven cloth. Leakage paths, both in axial and radial directions, are minimized or precluded.

Abstract: A high-pressure ratio turbocharger of this invention has a two-stage compressor section comprising a first-stage compressor impeller rotatably disposed in a first compressor housing, and a second-stage compressor impeller rotatably disposed in a second-stage compressor housing. The first and second stage compressor impellers are attached to a common shaft, and are positioned within respective compressor housing in a direction facing away from one another. A portion of the second-stage compressor housing is formed from a compressor backplate attached to a turbocharger center housing. A scroll seal is disposed between the first and second-stage compressor housings, and is interposed between the impellers to separate outlet air flow between each respective first and second-stage compressor chamber.

Abstract: A sealing element for a turbine of a gas turbine engine includes a radially inner surface region provided with an integrally formed seal structure comprising a plurality of radially inwardly projecting walls. The walls may be abradable and may define cells for receiving an abradable sealing material.

Abstract: A high-pressure ratio turbocharger of this invention has a two-stage compressor section comprising a first-stage compressor impeller rotatably disposed in a first compressor housing, and a second-stage compressor impeller rotatably disposed in a second-stage compressor housing. The first and second stage compressor impellers are attached to a common shaft, and are positioned within respective compressor housing in a direction facing away from one another. A portion of the second-stage compressor housing is formed from a compressor backplate attached to a turbocharger center housing. A scroll seal is disposed between the first and second-stage compressor housings, and is interposed between the impellers to separate outlet air flow between each respective first and second-stage compressor chamber.

Abstract: A device which can be utilized to temporarily seal substantially any opening on a turbine which is being assembled or repaired. The foreign material exclusion device includes a main body, preferably formed from a foamed polymer or rubber. The foreign material exclusion device is substantially elastic or resilient and can be compressed to fit into a desired opening and can be reexpanded to provide a snug fit about an opening. An extraction member is connected to the main body and is preferably utilized to remove the device from a portion of a cavity of a turbine.

Abstract: A method to facilitate sealing between a rotary component and a stationary component is provided. The rotary component includes at least one bucket secured thereon, the bucket having a flow admission side and a flow exit side. The method includes coupling a spill strip in a gap defined between the rotary and stationary component, wherein the spill strip has a substantially flat contact surface, and coupling a cover to a radially outer tip of the bucket, wherein a protrusion extends from the bucket cover to contact the substantially flat contact surface of the spill strip.

Abstract: A jacket ring for the low-pressure-turbine region of a gas turbine, having a plurality of lined-up segments which are arranged between a moving blade ring with shroud band and the casing of the gas turbine, which carry a run-in lining and which hold guide blades in a positive-locking manner, said guide blades being arranged upstream.

Abstract: A high-pressure ratio turbocharger of this invention has a two-stage compressor section comprising a first-stage compressor impeller rotatably disposed in a first compressor housing, and a second-stage compressor impeller rotatably disposed in a second compressor housing. The first and second stage compressor impellers are attached to a common shaft, and are positioned within respective compressor housing in a direction facing away from one another. A portion of the second compressor housing is formed from a compressor backplate attached to a turbocharger center housing. A scroll seal is disposed between the first and second compressor housings, and is interposed between the impellers to separate outlet air flow between each respective first and second compressor chamber.

Abstract: A seal arrangement for reducing the seal gaps within a rotary flow machine, preferably an axial turbomachine, having rotor blades and guide vanes, which are respectively arranged in at least one rotor blade row and guide vane row and have respective blade/vane roots (2,3) which protrude into fastening contours within the rotor blade and guide vane rows, is described. The invention is characterized in that a sealing element (4) in plastically deformable material is provided between at least two adjacent blade/vane roots (2,3) along a rotor blade row or guide vane row or between a blade/vane root (2,3) of a rotor blade or guide vane and a rotary flow machine component directly adjoining the blade/vane root.

Abstract: A sealing mechanism for a fluid pump comprises first and second seal members which are coaxially and radially oriented relative to each other, and are positioned between the rotating and non-rotating elements of the fluid pump to maintain a competent seal which is simple to assembly, maintain and repair or replace, and which also improves pump operation when compared to known sealing mechanisms for fluid pumps.

Abstract: The inner barrel of a turbine has a plurality of holes for receiving compressor discharge air and flowing such air within the inner barrel. A plurality of replaceable nozzles having internal bores of different diameters are selectively screw threaded into the openings of the inner barrel body enabling, with different diameters, a variation in the flow of compressor discharge air entering the inner barrel.

Abstract: A method for controlling fluid leakage between a first pressure region and a second pressure region within a gas turbine engine using a first sealing member and a second sealing member. The first sealing member is movably coupled to a portion of the gas turbine engine, and a space defined generally between a portion of the first sealing member and a portion of the second sealing member fluidly couples the first pressure region to the second pressure region. The method includes moving the first sealing member towards the second sealing member using fluid pressure within a portion of the engine, and, using the first and second sealing members, substantially controlling fluid leakage between the first pressure area and the second pressure area through the space generally without contacting the first sealing member with the second sealing member.

Abstract: The invention concerns a blood pump, in particular a ventricular cardiac support pump, with formed in a pump housing a blood chamber which is designed to hold a rotor rotatable about a rotor axis and at opposite ends in sections forms an inlet connectable with an inlet cannula, where an outlet from the blood chamber connectable with an outlet cannula extends in a direction perpendicular to the rotor axis, and where the rotor axis at its ends is mounted rotatably in mechanically active bearings provided in the area of the inlet concerned and connected with the pump housing.

Abstract: A steam turbine includes a stator supporting a plurality of turbine nozzles. The stator has shaped grooves for receiving a complementary-shaped nozzle hook formed on an end of each of the turbine nozzles. A rope seal is disposed in each interface between the nozzle hooks and the shaped grooves, respectively. The rope seal serves to seal a leakage path that may exist over the nozzle hooks between the nozzles and respective stator grooves.

Abstract: A biased, wear resistant seal assembly for sealing gas flow paths in a turbine system includes a planar shim having transverse legs at each end, a flattened leaf spring to urge the shim into sealing contact with the sealing surfaces of the turbine parts, and a shim protection material to avoid wear to the shim on the contact side. The shim protection material can include one or more metal fiber cloth layers secured to the shim, for example, by seam welding to a pair of rails or to the legs of the shim.

Abstract: A seal for use in a centrifugal pump of the type used for pumping an abrasive slurry, and having a sealing ring groove formed in the pump casing and means for supplying flushing water, comprising a radial seal having a sealing end, a water receiving end, and opposed sides and adapted for installation within the sealing ring groove, the radial seal having multiple openings formed therethrough for the passage of flushing water, The openings are dimensioned and located so that when flushing water is supplied to the water receiving end of the radial seal, the water flows through the openings, causing the radial seal to automatically moves to a self-compensating balanced position between the pump casing and a rotating pump impeller. This will reduce leakage between the pump casing and pump impeller and reduce wear of the pump surfaces.

Abstract: The invention relates to a turbine installation, especially a steam turbine installation. The inventive turbine installation comprises at least two partial turbines, each of the partial turbines having a rotor disk that extends along the main axis. Said rotor disks are rigidly interlinked to a shafting. At least one of the partial turbines has an inner housing that concentrically encloses the rotor disk and that is mounted so as to be axially displaceable in a bearing area. To allow for an axial displacement a push element transmits the axial force and is linked with the inner housing. In order to allow the inner housing to be axially displaced as easily as possible, the bearing area has a bearing device with a static friction and/or sliding friction that is so low that the axial misplacement that spontaneously occurs when the static friction is overcome during displacement of the inner housing is smaller 2 mm.

Abstract: A biased, wear resistant seal assembly for sealing gas flow paths in a turbine system includes a planar shim having transverse legs at each end, a flattened leaf spring to urge the shim into sealing contact with the sealing surfaces of the turbine parts, and a shim protection material to avoid wear to the shim on the contact side. The shim protection material can include one or more metal fiber cloth layers secured to the shim, for example, by seam welding to a pair of rails or to the legs of the shim.

Abstract: Upper and lower halves of the inner barrel of a compressor for a turbine are bolted to one another along a horizontal midline joint with metal-to-metal surface contact. Elongated grooves are provided in the engaging surfaces, with the upper groove having a depth greater than the depth of the lower groove. Elongated seals are provided in the grooves, including an elongated shim with a metallic woven covering on opposite sides, and margins having sealing edges. The depth of the seal is equal to or less than the depth of the upper groove and an adherent material maintains the seal in the upper groove during installation. In operation, the adherent material dissolves at temperatures above ambient and the seal drops by gravity to bear against the walls of the grooves in response to high pressure air leaking through any gap at the horizontal midline joint.