Abstract: A pressure activated flow path seal for a steam turbine is disclosed. In one embodiment a gap closure component is located about a rotary component and the stationary component of the steam turbine. A pressure differential activates the gap closure component to seal or reduce the radial clearance of a steam leakage path between the rotary component and the stationary component.

Abstract: A pump assembly with a rotatable rotor shaft (10), wherein the rotor shaft (10) includes at least one axial bearing (36, 40) and a radial bearing (30, 32), which are integrated into a common bearing assembly (16).

Abstract: A turbocharger, which is particularly suitable for a motor vehicle, includes: a rotor shaft with a turbine impeller and a compressor impeller disposed thereon. The rotor shaft has a roller bearing assembly for mounting in the housing of the turbocharger.

Abstract: A device for sealing a bearing housing, which holds lubricating oil, from which a rotor supported inside the housing of an exhaust gas turbocharger is guided into a compressor housing, loadable by a mass flow of a charger. The device includes a fixed partition with a wall extension, a sealing disk fastened on a shaft of the rotor, a separating gap arranged between the sealing disk and the wall extension, and a drip device connected to an oil-collecting channel and directs lubricating oil collected in the oil-collecting channel into an oil drain by gravity. The drip device includes a drain-off surface for lubricating oil, which has a large axial distance from a rotating sealing disk which delimits the separating gap. Lubricating oil which can penetrate into the separating gap is guided into an oil drain of the bearing housing without interacting with the sealing disk.

Abstract: Wind turbine provided with a bearing supporting a hub carrying rotor blades, the bearing comprising a rotational bearing race connected to the hub and a stationary bearing race, a lubrication area between the bearing races which area is confined at both ends by first seal rings sealing the gap between the rotational bearing race and stationary parts to form a lubrication barrier. At one or both ends of the lubrication area a redundant seal ring is arranged at a distance from the first seal ring in or near the gap to be sealed.

Abstract: An axial turbine for a gas turbine including a rotor blade cascade is provided. The rotor blade cascade is formed from rotor blades each including, a front edge, a blade tip, and an annular space wall that surrounds the rotor blade cascade and includes an annular space inner side, enabling the annular space wall to be arranged directly adjacent to the blade tip forming a radial gap between the covering of the blade tip and the annual space inner side. When the turbine is in operation, the area of the blade tip with the highest pressure load is disposed in the region of the front edges, and the rotor blades in the region of their front edges include a radial projection and the annular space wall includes on the annular space inner side, a peripheral radial recess that interacts with the radial projections such that a minimum is established in the direction of the main through-flow of the turbine.

Abstract: A plain bearing assembly for mounting a blade to a hub of a wind turbine includes an outer member mountable to one of the blade or hub, and an inner member mountable to the other of the blade or hub and movable relative to the outer member. The plain bearing further includes fluid cavities associated with one of the outer or inner member and arranged to confront the other of the outer or inner member. The fluid cavities are coupled to a pressure source for establishing a pressurized fluid film between the inner and outer members. A method includes monitoring at least one parameter of the fluid film, comparing the at least one parameter to a threshold criteria, and altering a dynamic state of the wind turbine and/or altering the state of the blade bearing assembly if the threshold criteria is exceeded.

Abstract: A centrifugal pump assembly with at least one impeller (8) and with a thrust bearing (44) which includes a rotating (50) and a stationary (48) bearing part. The rotating (50) as well as the stationary (48) bearing part are designed in a self-aligning manner.

Abstract: A blade bearing ring for turbocharger application in diesel engines is described, which consists of an iron-based alloy with an austenitic basic structure having dendritic carbide precipitations.

Abstract: The invention describes a holding disk for use in turbochargers, in particular for diesel engines, said holding disk consisting of an iron-based alloy having an austenitic base structure with dendritic carbide precipitations.

Abstract: One embodiment of the present invention is a unique turbomachinery device, a non-limiting example of which is a gas turbine engine. Another embodiment is a unique vane assembly for a turbomachinery device. Another embodiment is a unique seal assembly for a vane of a turbomachinery device. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for turbomachinery devices, and for vane assemblies and seal assemblies for turbomachinery devices. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.

Abstract: A stator-rotor assembly which includes at least one interface region between the stator and rotor is described. At least one stator or rotor surface in the interface region includes a pattern of inverted turbulators. The inverted turbulators restrict gas flow through a gap between the stator and the rotor. Various turbomachines which can contain such a stator-rotor assembly are also described. The disclosure also discusses methods to restrict gas flow through gaps in a stator-rotor assembly utilizing the inverted turbulators.

Abstract: A seal for stemming leakage flows between adjacent components (9, 20), especially of a gas turbine, has an elastically deformable, thin-walled sealing element (1) and a thin-walled cover element (13) which is U-shaped in cross section and between its legs (15) and its base (14) partially accommodates the sealing element (1). The legs (15) of the cover element (13) are arranged in the sealing arrangement, which features the seal, between two oppositely disposed walls (28) of the other component (9) in a movable manner relative to these walls (28) which, together with the sealing surface (8) of the other component (9), form a groove (27) which is U-shaped in cross section. Forces, which act laterally upon the seal, are absorbed by the cover element (13) and via the legs (15) are diverted into the other component (9) so that the integrity of the seal is maintained even in the case of lateral forces.

Abstract: A fluid energy machine is provided. The fluid energy machine includes a housing having a motor, an impeller, at least two radial bearings, and a shaft which extends along a shaft longitudinal axis and which supports the impeller and a rotor of the motor wherein the shaft is mounted in the radial bearings. The motor includes a stator which at least partially surrounds the rotor in the region of the motor. A gap which extends in the circumferential direction along the shaft longitudinal axis is formed between the rotor and stator and between the rotor and the radial bearings, which gap is at least partially filled with fluid. The motor is embodied as a bearing and is connected to a controller which activates the motor so that forces acting radially with respect to a shaft longitudinal axis can be exerted in addition to torques for driving the fluid energy machine.

Abstract: The invention relates to an exhaust-gas turbocharger (1) having a compressor housing (3), having a bearing housing (28) which can be connected at one end to the compressor housing (3) by means of a first fastening device (19), and having a turbine housing (2) which can be connected to the bearing housing (28) at the other end of the latter by means of a second fastening device (20), with the compressor housing (3), the bearing housing (28) and the turbine housing (2) extending along an exhaust-gas turbocharger longitudinal axis (R), wherein the second fastening device (20) is designed as a plug-and-twist connecting device, and a seal (25) is provided between the turbine housing (2) and the bearing housing (28).

Abstract: A gas turbine includes a turbine section; an annular combustor disposed upstream of the turbine section and configured to discharge a hot gas flow on an outlet side to the turbine section; an outer shell delimiting the combustor and splittable at a parting plane; a plenum enclosing the outer shell; a rotor; a turbine vane carrier encompassing the rotor; a plurality of stator vanes disposed on the vane carrier, and at least two sealing segments forming a ring, each of the at least two sealing segments having an inner edge and a head and a foot section and being movably mounted on the inner edge by the foot section to the outer shell and by the head section to the turbine vane carrier so as to mechanically connect the combustor to the turbine vane carrier.

Abstract: A propeller pod drive for a vessel has at least one driveshaft for driving a propeller, at least one radial bearing arrangement for receiving radial forces, at least one axial bearing arrangement for receiving axial forces of the driveshaft. A thrust collar is supported in axial direction on at least one side in axial direction at a guide device, and a supporting structure for arranging the at least one radial bearing arrangement and the axial bearing arrangement. The guide device has at least three, axial sliding segments arranged in a segment guide and each of which has a sliding surface in contact with the thrust collar.

Abstract: A centrifugal pump includes at least one impeller (4) and at least one sealing arrangement arranged between the impeller (4) and a housing wall. The sealing arrangement seals a suction side of the impeller (4) with respect to a pressure side of the impeller (4). The sealing arrangement including a seal (12) fastened on the impeller (4) in a rotationally fixed manner.

Abstract: A wind turbine is provided comprising a rotatable main shaft having a centre axis and being at least indirectly connected to a wind turbine rotor of the turbine and a main bearing supporting the rotatable main shaft at least indirectly against a first stationary part of the turbine, wherein fastening unit are provided for fastening the rotor to the first or a second stationary part of the turbine during replacement of the main bearing and tappet unit are provided which are able to act on the main bearing and permit a movement of the main bearing relatively to the first stationary part in the direction of the centre axis. A method for replacement of a main bearing is also provided.

Abstract: A nozzle guide vane for a gas turbine engine comprises a hollow ceramic vane member which includes an aerofoil portion and ceramic platforms. The ceramic vane member is supported by engagement of its interior surface with external supporting surfaces on a metallic load-bearing spine adapted to be supported from fixed structure of the engine.

Abstract: Roller bearings, and struts and gas turbine engines using such bearings are provided. In this regard, a representative roller bearing for a gas turbine engine includes: a roller having a rolling surface and an end; a race having a flange and defining a raceway, the raceway terminating at the flange, the raceway being operative to receive the roller such that the rolling surface of the roller engages in rolling contact with the raceway; and a hard coating applied to the flange such that the end of the roller engages in sliding contact with the coating.

Abstract: A pressure equalization system reduces or eliminates a pressure differential across supercharger rotor shaft seals. Under high boost, rotor shaft seals often fail, allowing hot compressed air into an oil lubricated space containing rotor bearings and gears (and vented to ambient pressure), reducing oil lubricating effectiveness and resulting in increased wear and failure. Under low or non boost operation, the pressure differential is reversed causing the lubricating oil to leak into the supercharger interior and accelerated rotor seal wear. The pressure equalization system includes flow restrictive seals on both rotor shafts, separated from the rotor shaft seals by vented spaces, thereby isolating the rotor shaft seals from boost or vacuum in the supercharger interior and reducing or eliminating the pressure differential across the rotor shaft seals. Maintaining close to atmospheric pressure on both sides of the rotor shaft seals during boost and vacuum operation reduces wear and failures.

Abstract: A shroud rail for retaining a feather seal in a vane shroud of a gas turbine engine comprises a slot for, receiving the feather seal, and a chamfer rail pocket for lightening the shroud rail. The slot traverses the vane shroud and includes a slot base extending from a leading edge to a trailing edge of the shroud rail, and a slot wall extending generally perpendicularly from the slot base. The chamfer rail pocket comprises a pocket wall extending along the slot wall, and a chamfer wall extending from the pocket wall at an angle oblique to the slot base.

Abstract: A method is provided for engineering a single crystal cast gas turbine engine first component for cooperating with a second component. An at least local first operational stress on the first component is determined. The first operational stress has a first direction. A crystal orientation within the component or a physical configuration of the component is selected so that the first operational stress produces a desired engagement of the first component with the second component associated with either a negative Poisson's effect or high Poisson's effect in a second direction. Single crystal or highly textured iron- and nickel-base alloys enable one to use such effect in high temperature and/or corrosive environments.

Abstract: A gas turbine engine sealing arrangement which includes a combustor liner establishing a combustion area and a turbine nozzle configured to receive a portion of a combustor liner. A sealing ring arrangement is configured to seal with the turbine nozzle to control fluid flow from the combustion area and reduce leakage.

Abstract: A seal assembly (60) for sealing first and second static parts (40A, 40B) with opposed slots (44A, 44B) together forming a pocket (46). The seal assembly (60) comprises a floor strip (70) positioned adjacent the pocket's floor (48) and a ceiling strip (80) positioned adjacent the pocket's ceiling (50). A connection (90) of the strips' central portions (72, 82) provides a flat hinge between cooperating hinge portions (76, 86). A first set of the hinge portions (76A-86A) converge for insertion into the first slot (44A) and a second set of hinge portions (76B-96B) converge for insertion into the second slot (44B). After such slot insertion and pocket installation, the converged hinge portions (76A-86A, 76B-86B) resiliently diverge within the pocket to seat the floor strip's end portions (74A, 74B) against the pocket's floor (48) and to seat the ceiling strip's end portions (84A, 84B) against the pocket's ceiling (50).

Abstract: A bearing system for a rotor in rotating machines, such as compressors, pumps, turbines, expanders, has points of bearing and sealing for the rotor each being in the form of a combined bearing and sealing formed by a stator situated within a rotating machine house and surrounding the rotor. The stator is formed with a bore, whereby an annular clearance is created between stator and rotor, and the bore is having sectional area gradually increasing in the direction of larger pressure within the rotating machine.

Abstract: The present invention relates to an oil-free turbocharger assembly using an airfoil bearing that may be useful in high speed conditions. The assembly can be cooled easily. A heat-proof coating can also be easily applied to the turbo charger's rotating shaft. In one embodiment, an oil-free turbocharger assembly has a constant distance between a journal portion and a rotating shaft so that the mass of the rotating body can be minimized and the rotating body assembly can have a small moment of inertia. The turbocharger in some embodiments of the invention may be cooled by a refrigerant which improves cooling efficiency. Each part of the rotating body assembly in some embodiments may be individually treated with a heat-proof process so that productivity can be improved.

Abstract: The invention relates to an axial bearing (10) comprising at least one or more segments (18) on each of the front side (22) and the rear side (26) thereof, wherein the segments (18) on the opposite sides (22, 26) each are disposed at least partially offset from each other.

Abstract: A turbocharger with a variable turbine geometry, includes at least one rolling body element respectively disposed on an associated fixing element for the variable turbine geometry. A device for adjusting the variable turbine geometry can roll off on the respective rolling body element.

Abstract: A sealing arrangement for use in a turbine engine having ceramic components. The sealing arrangement is retained in a seal gap formed between adjacent segments and is compliant to accommodate variations in the size of the seal gap as the adjacent segments move relative to one another.

Abstract: A centrifugal supercharger is provided. One embodiment of the supercharger comprises a two-piece housing wherein a parting area is substantially aligned with a rotational axis of a drive or impeller shaft. Another embodiment comprises a sleeve, or intermediate member disposed substantially between the housing and a bearing assembly(s) located within the supercharger housing. Another embodiment comprises a disengagement device located between the supercharger impeller and the engine. The disengagement device allows selective disengagement of the impeller from the engine. This Abstract is provided for the sole purpose of complying with the Abstract requirement rules that allow a reader to quickly ascertain the subject matter of the disclosure contained therein. This Abstract is submitted with the explicit understanding that it will not be used to interpret or to limit the scope or the meaning of the claims.

Abstract: The invention relates to a compressor, particularly a high pressure compressor, of a gas turbine, particularly of a gas turbine aircraft engine, having at least one rotating blade ring on the rotor side, and having at least one guide blade ring on the stator side, wherein the, or each, guide blade ring is formed of a plurality of guide blade segments, and wherein each guide blade segment is formed of a plurality of individual blades. According to the invention, adjacent individual blades (11, 12; 12, 13; 13, 14) are permanently connected to each other within each guide blade segment (10) of at least one guide blade ring on opposing surfaces positioned radially outward, whereas the same are not connected to each other on opposing surfaces positioned radially inward.

Abstract: An inner air seal carrier for use in a gas turbine engine having an inlet guide vane surge retainer comprises a body, a stationary sealing element and an outcropping. The body secures around an inlet guide vane inner diameter shroud. The stationary sealing element is disposed on a radially inward face of the body for engaging with a rotatable sealing element of a compressor rotor. The outcropping is positioned on the radially inward face of the body forward of the stationary sealing element for engaging with the surge retainer.

Abstract: A compressor has a diffuser section with one or more detachable wall portions that define a diffuser surface. The wall portions may be detachably connected to an intermediate portion of the compressor housing between the inlet and outlet and/or to the bearing housing of a turbocharger to which the compressor housing is connected. The diffuser wall portions can be easily detached once the compressor housing is removed so as to allow cleaning of deposits or simple replacement. This provides for easy servicing to avoid the compressor performance being compromised by a built up of deposits and particulates on the diffuser surfaces that is a particular problem in turbochargers that receive recirculated crank case ventilation gases from the engine.

Abstract: A low pressure turbine rotor disk for a small twin spool gas turbine engine in which the rotor disk includes a forward side cavity large enough to allow for the bearing assembly that rotatably supports the rotor disk to fit within the cavity in order to shorten the axial distance between the bearings that support the inner rotor shaft on which the turbine rotor disk is secured. Minimizing the bearings spacing allows for a high critical speed for the inner rotor shaft and therefore allows for the small twin spool gas turbine engine to operate at this small scale. The turbine rotor disk also includes a plurality of axial aligned cooling air holes to allow for cooling air from the bearings to flow out from the aft end of the rotor disk. The inner surface of the cavity is an annular surface that forms a seal with knife edges extending outward from the bearing support plate also located within the cavity.

Abstract: A seal and method of making seals utilises folds in order to form creases in a length of material such that the creases reinforce individual seal elements or surfaces whilst perforations or slots in a seal edge allow air leakage from one side of the seal element or surface to the other. Thus, air pressurisation can take place between spaced seal elements or surfaces and this allows air flotation or riding of a rotating component relative to a static housing component. The perforations are typically graduated from the seal edge in order to provide the best pressurisation and air-riding effect for proximity or gap control between the sealing edge and the rotating component surface. The slots effectively provide flexibility to the sealing edge such that the seal component emulates a brush seal.

Abstract: A pattern of depressions (36) in a sealing surface (34) on a CMC wall (32) of gas turbine ring segment (30) allows minimum clearance against turbine blades tips, and thus maximizes working gas sealing. An array of depressions (36) on the surface (34) increases abradability of the surface (34) by blade tip contact during zero clearance conditions and reduces blade tip damage. The depressions (36) are unconnected, preventing bypass of the working gas around the blade tips. A desired abradable surface geometry may be formed in a stacked laminate wall construction (40-43, 52) by staggered laminate edge profiles (50, 52) or by machining of depressions (36, 54) after construction.

Abstract: A mounting structure for an air separator in a gas turbine includes an air separator and a rotor blade rotary disk. The air separator includes a cylindrical member with a flange at one end. The rotor blade rotary disk has on its outer face a disk recess portion forming an annular recess around the axial center of the rotor. A sealing face is formed on a contact face between a flange outer peripheral face that is provided on an outer periphery of the flange to be parallel to the axial center of the rotor and a disk recess inner peripheral face opposed to the flange outer peripheral face, that is provided on the disk recess portion and is parallel to the axial center of the rotor and formed around the axial center in an annular shape.

Abstract: A two-row tapered roller bearing includes an outer ring (1) having an outer diameter of at least one meter, a first inner ring (2) and a second inner ring (3) that is disposed axially adjacent the first inner ring (2). A first set of conically-formed roller bodies (4) roll between the outer ring (1) and the first inner ring (2) and a second set of conically-formed roller bodies (5) are disposed axially adjacent the first roller bodies (4) and roll between the outer ring (1) and the second inner ring (3). A first sealing ring (11) is disposed axially adjacent the outer ring (1), is connected with the outer ring (1) and slips on a slip surface (16) of the first inner ring (2) in a contacting manner.

Abstract: A seal assembly for a gas turbine engine including a seal member and an interstage seal ring including an axially forward member coupled to a first radially inward surface of a first disk and an axially aft member coupled to a second radially inward surface of a second disk, wherein the seal ring is configured to move in an axial direction while the upstream and downstream arms are coupled to the first and second disk respectively.

Abstract: Turbulence of exhaust gas in a turbine impeller outlet is reduced with a simple structure to improve efficiency of a turbine. A sealing device 25 for prevention of exhaust gas in a scroll passage 8 from leaking via a gap 19 to a turbine impeller 4 is arranged upstream, in a travel direction of the exhaust gas, of through-holes 24 via which the vane shafts 16b extend through a rear exhaust introduction wall 11, whereby pressure P2 in a gap 19 communicating with the through-holes 24 of the rear wall 11 is kept lower than pressure P1 in an exhaust nozzle 9 so as to displace nozzle vanes 15 to the rear wall 11.

Abstract: A bearing apparatus is disclosed. Such a bearing apparatus may comprise a rotor including at least one bearing element mounted to the rotor and a stator including at least one bearing element mounted to the stator. At least one compliant member may be positioned between at least one selected bearing element of the at least one bearing element mounted to the rotor and the at least one bearing element mounted to the stator. Mechanical systems including such a bearing apparatus are disclosed, such as, for example, a motor for use in subterranean drilling. A method of assembling a bearing apparatus is disclosed. More specifically, a rotor and a stator each including at least one bearing element may be provided and a compressive force may be applied to the rotor and the stator to compress the bearing surfaces of the rotor and the stator against one another. Rotors and stators are disclosed.

Abstract: An apparatus for adjusting a thrust load on a rotor assembly of a gas turbine engine includes an impeller rear cavity defined between a rear face of an impeller of the rotor assembly and a stationary wall spaced axially apart from the rear surface of the impeller. A pressurized air flow with a tangential velocity is introduced into the impeller rear cavity at a tip of the impeller to pressurize the cavity. Means are provided in the cavity for directly interfering with the tangential velocity of the pressurized air flow to affect an average static pressure of the pressurized air flow within the cavity in order to adjust the thrust load on the rotor assembly caused by the average static pressure in the cavity.

Abstract: The present application provides an angel wing seal for a turbine bucket. The angel wing seal may include a first wing with a sinusoidally-shaped outer edge and a number of wing teeth positioned thereon.

Abstract: A composite component such as a fan rear seal comprises a hub and a body of composite material which is moulded over the outer periphery of the hub. The body is formed from a preform of fibre reinforcement impregnated with a resin, in a compression moulding process. The body has an annular projection provided with a sealing surface. The sealing surface may comprise circumferential fins, or may be a surface of, for example, an abradable seal insert moulded into the composite material of the body.

Abstract: A shaft for a gas turbine engine is provided that includes a first shaft section, a second shaft section, a first flexible linkage, and a second flexible linkage. The first shaft section extends between a forward axial end and an aft axial end along a first axial centerline. The second shaft section extends between a forward axial end and an aft axial end along a second axial centerline. The first flexible linkage includes a bridge section connected between a first diaphragm and a second diaphragm. The first diaphragm is connected to the aft axial end of the first shaft section. The second diaphragm is connected to the forward axial end of the second shaft section. The second flexible linkage includes a diaphragm and a hub. The second flexible linkage diaphragm cantilevers radially outwardly from an inner radial end to an outer radial end, and is connected to the aft axial end of the second shaft section.

Abstract: A fluid pump comprising a pump body, a low pressure impeller, a high pressure impeller, impeller seal means separating the inlet side of the low pressure impeller from its pressure side, a pump priming system, and a pump priming conduit provided through the low pressure impeller radially inboard of the impeller seal means. The high pressure impeller is preferably provided within a cavity, defined by an impeller recess and a cover plate. A wear ring is preferably provided between the low pressure impeller and the inboard end of the cover plate. The pump priming conduit preferably comprises: first and second axial bores through the pump body; a radial bore and two axial holes through the cover plate; an axial hole through the rear wear ring; a cavity between the wear ring and the low pressure impeller; and axial holes through the low pressure impeller, connecting the cavity to the suction side of the low pressure impeller.

Abstract: Jet engine (1), especially for an aircraft, with at least one hollow shaft (7) and/or low pressure shaft (8) rotatably supported in at least one bearing arrangement about a center axis, on which shaft at least respectively one high and/or low pressure compressor (2, 12) as well as at least respectively one high and/or low pressure turbine is arranged, whereby the jet engine (1) further comprises an electromechanical unit (10), in order to provide at least a motor function for starting the jet engine (1) and/or a generator function for the power supply, whereby the electromechanical unit (10) is arranged centrally about the center axis, whereby the electromechanical unit (10) furthermore encompasses the function of an active magnetic bearing arrangement, in order to form at least one bearing arrangement of the at least one hollow shaft (7) and/or low pressure shaft (8), and whereby the electromechanical unit (10) is embodied as a transverse flux machine.

Abstract: A method and apparatus to reduce the axial thrust in rotary machines such as compressors, centrifugal pumps, turbines, etc. includes providing additional peripheral restrictive means (7) attached at the peripheral portion of the disk forming the subdividing means (4) on the side facing the rotating rotor (2). An additional ring element at the periphery of the subdividing means forms additional radial (11) and axial restrictive means (15). Such peripheral restrictive means (7, 11 and 15) function as sealing dams, which combined with the outward flow induced by the rotating impeller, form self-pressurizing hydrodynamic bearings in the axial and radial planes, improving rotordynamic stability. Additionally, a stationary ring element in the center of the cavity forms a seal with the rotor, reducing leakage to suction.