Abstract: A turbomachine has a shaft mounted in a shaft housing, and a rotor in a rotor housing at one end of the shaft, for compression, expansion, or transport of a working gas. The shaft is mounted by hydrostatic, gas-lubricated bearings that have a connector to a compressed gas line that is connected with a pressure region of the turbomachine. A portion of the gas that is passed from the pressure region is applied to the bearing. The shaft is mounted so that the bearing effect is at least extensively independent of the rotational speed of the shaft, thereby guaranteeing support of the shaft during startup of the turbomachine, and good rigidity and low sensitivity to pressure surge stresses. The pressure in the connector to the compressed gas line is at least 5 bar greater than the pressure in the region of the ventilation connector.

Abstract: An axial flow turbine stage structure has: an annular diaphragm inner ring; an annular diaphragm outer ring arranged radially outside and coaxially with the diaphragm inner ring and separated from the diaphragm inner ring by an annular flow path interposed between them; stationary blades arranged peripherally at intervals in the annular flow path and rigidly secured to the diaphragm inner ring and the diaphragm outer ring; and moving blades rigidly secured to the outer periphery of a rotatable rotor and arranged peripherally at intervals respectively at axially downstream sides of the stationary blades. Through holes are formed in the diaphragm outer ring so as to allow axial upstream side and axially downstream side of the stationary blades to communicate with each other.

Abstract: A steam turbine of an embodiment includes: a nozzle box having a circular ring-shaped steam passage into which steam is led from a steam inlet pipe and having, on a downstream portion of the steam passage, a plurality of first-stage nozzles in a circumferential direction; and a second-stage nozzle side structure combined with the nozzle box and having a plurality of at least second-stage nozzles in a circumferential direction. Further, in the respective nozzle box and second-stage nozzle side structure, there are provided at least a pair of abutment surfaces for sealing which are not parallel to a turbine rotor axis and abutting each other. Furthermore, a seal member is provided in a part of a gap between the nozzle box and the second-stage nozzle side structure, the gap being formed by combining the nozzle box and the second-stage nozzle side 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: The present invention provides a water lubricated line shaft bearing assembly, comprising an outer annular steel shell and an inner layer made of low friction material attached to the outer shell, the inner layer having a non-uniform thickness which is formed with wall portions of increased thickness defining a plurality of shaft engaging portions and with wall portions of reduced thickness defining a plurality of lubricant passages. The shaft engaging portions are capable of being journalled on a line shaft adapted to drive a downhole geothermal production pump and the steel shell is engageable with an inner wall of a lubrication tube vertically extending through a water column through which pumped geothermal fluid is delivered, lubrication water bled from the pumped geothermal fluid being used to supply lubrication water through the lubricant passages.

Abstract: An oil-free turbo vacuum pump is capable of evacuating gas in a chamber from atmospheric pressure to high vacuum. The turbo vacuum pump includes a pumping section having rotor blades and stator blades which are disposed alternately in a casing, a main shaft for supporting the rotor blades, and a bearing and motor section having a motor for rotating the main shaft and a bearing mechanism for supporting the main shaft rotatably. A gas bearing is used as a bearing for supporting the main shaft in a thrust direction, spiral grooves are formed in both surfaces of a stationary part of the gas bearing, and the stationary part having the spiral grooves is placed between an upper rotating part and a lower rotating part which are fixed to the main shaft.

Abstract: A shaft assembly for a gas turbine engine includes a shaft, an annular fluid collection cavity, and a bearing. The shaft is rotatable around an axially extending shaft centerline. The annular fluid collection cavity is formed by an axial panel extending between a forward radial panel and an aft radial panel. The aft radial panel includes a plurality of fluid apertures, each fluid aperture having a center disposed at a first radius from the shaft centerline. The bearing includes an inner race having a shaft mounting surface and a plurality of axially extending race fluid passages. The shaft mounting surface is engaged with an exterior surface of the shaft, and is disposed at a second radius from the shaft centerline, wherein the second radius is less than the first radius. At least some of the axially extending race fluid passages are fluidly connected with at least some of the fluid apertures in the aft radial panel.

Abstract: An oil-free turbo vacuum pump is capable of evacuating gas in a chamber from atmospheric pressure to high vacuum. The turbo vacuum pump includes a pumping section having rotor blades and stator blades which are disposed alternately in a casing, and a main shaft for supporting the rotor blades. A gas bearing is used as a bearing for supporting the main shaft in a thrust direction, spiral grooves are formed in both surfaces of a stationary part of the gas bearing, and the stationary part having the spiral grooves is placed between an upper rotating part and a lower rotating part which are fixed to the main shaft. A thrust magnetic bearing for canceling out a thrust force generated by the differential pressure between a discharge side and an intake side by an evacuation action of the pumping suction is provided.

Abstract: A high-speed turbomachine includes a magnetic bearing (22, 23) and a retainer bearing for mounting the rotor. The retainer bearing is embodied as a sliding bearing (26, 27) and encompasses a bearing shell (28) at the stator end, a bearing shaft (20) at the rotor end, and an intermediate bushing (30) between the bearing shell (28) and the bearing shaft (20). The intermediate bushing (30) is spaced apart from both the bearing shaft (20) and the bearing shell (28) by a circular gap (33, 34). The intermediate bushing (30) is rotatable relative to the bearing shell (28) and the bearing shaft (20). As a result of this design, the sliding bearing (26) is provided with two pairs of sliding surfaces, onto which all occurring dynamic forces are distributed such that wear is significantly reduced, thus allowing sliding bearings to be used as retainer bearings in a magnetically mounted high-speed turbomachine.

Abstract: A gas turbine engine (10) comprising a first turbine (19) and a first compressor (13) mounted on a first shaft (26) and a bearing arrangement (52, 34) supporting the shaft (26), the bearing arrangement is subject to a total end load and comprises a fixed bearing (34), a load share bearing (52) and a bearing end load management system (50) that is capable of applying a variable load to the load share bearing to manage total end load between the bearings. The bearing end load management system comprises a static diaphragm (54) that defines part of a chamber (56) and that is coupled to the load share bearing whereby increased pressurization of the chamber loads the diaphragm which in turn increases the proportion of the total end load on the load share bearing.

Abstract: An inflatable sealing assembly for sealing between an intake section of a turbine engine and an air inlet ring of a vehicle. The inflatable sealing assembly including a seal holder coupled to the intake section of the engine and having a first inflatable seal, a second inflatable seal, and a closed cell foam material disposed therein. The first inflatable seal and the second inflatable seal are configured when inflated to provide a seal between the intake section of the turbine engine and the air inlet ring of the vehicle and prevent foreign object debris and/or water from entering the turbine engine.

Abstract: A sealing assembly configured to seal a rotating shaft of a turbo machine having a high pressure process gas, comprising a housing defining a bore configured to receive the rotating shaft and sealing assembly, wherein the housing is mounted to a casing of the turbo machine; a first sealing stage comprising a single dry gas seal and configured to blow down the high pressure process gas to a lower pressure; a labyrinth seal mounted longitudinally outward from the first sealing stage; and a second sealing stage mounted longitudinally outward from the labyrinth seal, wherein the second sealing stage comprises a tandem dry gas seal having a primary dry gas seal and a secondary dry gas seal axially spaced with an intermediate labyrinth seal.

Abstract: A sealing assembly is provided for sealing against a component. The sealing assembly comprises a seal carrier and a continuous seal element that is attached to the seal carrier at at least two discrete positions of attachment. The seal element is provided with a sealing surface that is arranged to seal against the component. The seal element is further provided with a thermal expansion slot that is located between the discrete positions of attachment and which extends from a first edge of the seal element over a portion of the width of the seal element. This allows the seal carrier and seal element to thermally expand in the length direction at different rates.

Abstract: A gap seal (9) radially seals a gap (8) which extends axially and radially between two blades (1, 2) of a turbomachine which are adjacent in the circumferential direction (3). The two blades (1, 2) have, in each case, an axially extending longitudinal slot (10, 11), which is open towards the gap (8), on its respective blade root (6, 7). A band-form or strip-form sealing element (12) engages with its longitudinal sides (13, 14) in the two longitudinal slots (10, 11) and bridges the gap (8). The one blade (1) has a projection (15) on its blade root (6), which projects from the blade root (6) in the circumferential direction (3) and extends in the circumferential direction (3) and radially, at least in the region of the respective longitudinal slot (10), and bridges an axial longitudinal end of the gap (8) in the process. The other blade (2) has a step-shaped recess (16) on its blade root (7), complementary to the projection (15) of the one blade (1) and in which the projection engages.

Abstract: A spindle device driven by driving fluid, having accurate rotation and superior quietness. The device includes a stator having at least one inlet for introducing the driving fluid, a rotor having at least one flange arranged outside of the stator and provided with nozzles for jetting the driving fluid, and a static-pressure fluid bearing for rotatably supporting the rotor with respect to the stator. The stator has a first inner path for conducting the driving fluid introduced from the inlet to the rotor and the rotor has a second inner path communicating with the first inner path of the stator for conducting the driving fluid to the nozzles. The driving fluid introduced from the inlet of the stator is jetted from the nozzles of the rotor through the first and second inner paths to rotate the rotor.

Abstract: A turbo compressor is provided including: a pump which sends lubricant stored in an oil tank having an open portion; and a control valve which adjusts the flow rate of the lubricant returning to the oil tank by dividing the stream of the lubricant sent from the pump; and an oil tank cover which blocks the open portion and is provided with an installation portion for the control valve, wherein the oil tank cover includes at least one of a first passage opened from the installation portion and allowing the stream of the lubricant sent from the pump to be divided and flow toward the control valve and a second passage opened from the installation portion and allowing the lubricant to flow from the control valve toward the oil tank.

Abstract: A supercharger for an internal combustion engine having an internal reservoir adapted to receive a supply of lubricating oil. An oil slinger is mounted on the impeller shaft for rotation therewith that extends into the reservoir for collecting and slinging lubricating oil onto the supercharger bearings, shafts and the drive and impeller gears. A baffle assembly is carried by the interior of the supercharger housing for controlling the volume and flow of lubricating oil onto said gears and bearings and directing oil flow therefrom back into said reservoir to prevent excessive lubrication buildup on the gears and the deleterious effects that result therefrom.

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 pressure balance seal includes a sealing surface facing an inward radial direction, and a stator interface comprising at least one surface interfacing with a stator. The pressure balance seal further includes a friction reducing feature. The friction reducing feature includes a cavity on the sealing surface. The cavity is configured to receive a fluid such that a normal force acting on the pressure balance seal is counterbalanced by a force generated by a pressure of the fluid.

Abstract: A sealing member has a first portion. The first portion has a central axis, a first peripheral surface extending in a direction parallel to the central axis, and a central aperture. A first wall portion of a groove has a recess communicated with the first opening of the first channel. The recess has a second peripheral surface complementary to the first peripheral surface of the first portion of the sealing member. The first portion of the sealing member moves radially toward and away from the rotational axis as the first peripheral surface of the sealing member defines and maintains a first sealing contact with the second peripheral surface of the recess. The sealing member moves radially outwardly and thereby makes a second sealing contact surrounding the second opening of the second channel to establish a communication between the first and second openings.

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 hermetic compressor includes a hermetic container arranged to store lubricating oil, a motor element accommodated in the hermetic container, an oil-feeding mechanism arranged to carry the lubricating oil, and a centrifugal pump arranged to carry the lubricating oil to the oil-feeding mechanism. The centrifugal pump includes a cylindrical portion having a hollow opening at the opening, and an aperture plate having a suction aperture formed therein. The aperture plate has an inner edge facing the suction aperture, and an outer edge of the aperture plate contacting an inner surface of the cylindrical portion. A portion of the aperture plate between the inner edge and the outer edge of the aperture plate is positioned more outward from the cylindrical portion than the inner edge and the outer edge are. This hermetic compressor does not produce fine metal powder during manufactured, having high reliability.

Abstract: A supercharger lubricating structure for an internal combustion engine is provided that can supply oil to a supercharger through a short oil passage without use of external piping and downsize a lubricating oil pump. A supercharger lubricating structure for an internal combustion engine can be characterized by the following: A rotating shaft can be connected to a crankshaft via a joint. A connection pipe can be insertably passed through the crankshaft and the rotating shaft to allow an intra-crankshaft oil-feed passage and an intra-rotating-shaft oil-feed passage to communicate with each other. An eccentric shaft portion can be provided on the rotating shaft. A supercharger composed of an orbiting movable scroll and front and rear fixed scrolls can be provided on the eccentric shaft portion via needle bearings. The front and rear fixed scrolls can be provided with ball bearings and the needle bearing supporting the rotating shaft.

Abstract: A gas turbine includes a compressor, a turbine downstream of the compressor having stators, and a rotor connecting the compressor to the turbine. The rotor includes rotor cavities. A supply plenum containing a process by-product gas and a control valve is connected to at least one of the rotor cavities to supply the process by-product gas to at least one of the rotor cavities. A process for operating a gas turbine having a compressor and a turbine includes connecting the compressor to the turbine by a rotor, creating cavities in the rotor, and injecting a process by-product gas into at least one of the cavities. The process further includes regulating the flow of the process by-product gas into at least one of the cavities according to a pre-programmed parameter.

Abstract: Turbine apparatus for a hydroelectric power station, with a turbine impeller, which is capable of rotating about a turbine rotary spindle, which is in particular arranged vertically, with turbine blades (4), which are fitted at an angle with respect to the turbine impeller (3), in particular a fixed angle, with a generator, which converts the mechanical rotation energy of the turbine impeller into electrical energy, wherein the generator is in particular an annular generator (5), with an annular rotor (6) and a stator (7), which is correspondingly arranged in annular fashion, wherein the turbine rotary spindle (2) is coupled to the rotor (6) in such a way that it is fixed against rotation, and the rotation about the turbine rotary spindle (2) takes place by means of a hollow shaft (8), with a pot-like receptacle (9), into which a fixed bearing journal (10) with movable bearings (11) arranged around it is inserted, in particular directly, and the turbine impeller (3) and the rotor (6) are capable of rotating a

Abstract: A side seal for sealing the side edges of adjacent combustors of a turbine engine include extended ends. The extended ends of the side seal abut and seal against inner and outer circumferential seals to prevent leakage of combustion gases.

Abstract: A sealing element for sealing a component gap with respect to a flow, in particular for use in a fluid-flow machine, specifically in a turbomachine is provided. In addition a fluid-flow machine is provided including such a sealing element for sealing a component gap. The sealing element includes a hollow profile enclosing a cavity. Arranged in the hollow profile are a first opening and a second opening, which are spaced apart from each other in the longitudinal direction of the hollow profile. The first opening is formed as an inlet opening for a cooling fluid into the cavity of the hollow profile, the second opening is formed as an outlet opening for the cooling fluid from the cavity of the hollow profile. With the sealing element arranged in a fluid-flow machine, the sealing element can consequently be internally cooled by means of the cooling fluid. Furthermore, the sealing element uses the pressure gradient occurring in the flow in the direction of flow to form a stable cooling fluid flow.

Abstract: A process fluid communication system includes a fluid source in communication with a process seal and a gearbox seal to communicate a pumping medium into a turbomachinery housing and a gearbox housing through the process seal and the gearbox seal.

Abstract: The present application thus provides for a turbine component cooling system. The component cooling system may include a turbine component, an airflow passing adjacent to the turbine component, and a seal positioned adjacent to the turbine component. The seal may include a number of apertures so as to allow the airflow to pass therethrough.

Abstract: An electrically controlled turbocharger has a motor mounted on a shaft in a motor housing between a turbine and compressor. Oil is sprayed onto the motor stator to cool the stator. An oil gallery is disposed above the stator to receive lubricating oil and contains apertures that perform as jets to allow oil to be sprayed directly on the motor stator. A coolant jacket is formed in the turbocharger housing between the turbine and the motor to allow liquid coolant to circulate therein and dissipate heat from the turbine end prior to reaching the motor components. Other embodiments provide for a stator component to be submerged in flowing cooling oil.

Abstract: In a rotodynamic pump, a seal chamber conditioning valve mechanism is positioned at least partially within the seal chamber of the pump to selectively and intermittently deliver fluid to or discharge contents from the seal chamber to modify the condition or content of the seal chamber and effectively protect the mechanical seal from failure due to, for example, built up solids or the presence of air. The conditioning valve mechanism may be actuated by a control device in communication with monitoring apparatus that determines the condition of the seal chamber, and particularly the mechanical seal face.

Abstract: Disclosed is a solution to automate a seal oil float trap by-pass for a hydrogen cooled generator. An automated by-pass system is coupled to an existing manual by-pass system for a float trap for a hydrogen cooled generator. The automated by-pass system includes at least one solenoid valve and a controller that controls opening and closing of the solenoid valve. The automated by-pass system can also include manual valves, orifices and limit switches. The controller activates the solenoid valve to allow the seal oil to drain. The controller can also provide a notification alarm that the hydrogen cooled generator is being purged.

Abstract: A fluidic rim seal system can be provided between a neighboring stationary and rotatable components in the turbine section of a turbine engine. For instance, the stationary component can be an inner shroud associated with a vane. The inner shroud can include a groove that extends circumferentially about the shroud. The rotatable component can be a blade cover plate. The blade cover plate can include a protrusion that culminates at a tip. One or more passages can extend through the protrusion. The passages can have an inlet in fluid communication with a coolant source and an outlet at the tip. A tip region of the protrusion is received in the groove. During engine operation, an air barrier is formed in the groove by the air discharging from the outlet. This air also provides cooling to the protrusion as well as a portion of the inner shroud.

Abstract: A cooling system has a drive motor which is to be cooled by a cooling medium. A cooling medium circuit conducts the cooling medium. A hydrodynamic machine comprising a working space can be filled with a working medium. The working medium is the cooling medium, and the hydrodynamic machine has a seal which is cooled and/or lubricated by the cooling medium. A cooling medium pump for circulating the cooling medium is in the cooling medium circuit. A pick-off is in the cooling medium circuit in the region of the cooling medium pump. Via the pick-off, the cooling medium is branched out of the cooling medium circuit. The branched-off cooling medium is conducted directly through or past the seal to cool and/or lubricate the latter, and the cooling medium which is conducted through or past the seal is supplied to the cooling medium circuit upstream or downstream of the working space.

Abstract: A turbine adapted to be constrained within a flow of fluid is disclosed. The turbine comprises a stator adapted to be constrained within a flow of fluid, and a rotor defining an aperture and having a plurality of rotor blades (10) protruding from a peripheral region of the rotor into the aperture. The rotor is adapted to be rotatably mounted to the stator such that movement of fluid through the aperture causes rotation of the rotor relative to the stator. Electricity is generated as a result of rotation of the rotor relative to the stator.

Abstract: The subject invention pertains to a method and apparatus for an orientation independent compressor. The subject compressor can be part of a vapor compression cycle system, and can use one or more of a variety of working fluids, including, but not limited to, refrigerants such as r-134a, r-22, CO2, and NH3. Embodiments of the compressor can utilize positive displacement means to compress the vapor. In a specific embodiment, the compressor can incorporate an oil-lubricated rotary lobed type positive displacement compressor. In a further specific embodiment, the working fluid can be a refrigerant, such as r-134a, incorporating entrained oil, such as miscible lubricating oils. An example of such a miscible lubricating oil that can be used is polyester (POE) oil.

Abstract: A blade outer air seal for being positioned radially outwardly of a gas turbine blade has at least one cooling air passage with a dividing wall dividing the at least one cooling air passage into two separate flow paths. The dividing wall does not extend throughout an entire length of the blade outer air seal of the first dimension.

Abstract: A method for assembling a gas or steam turbine is provided. The method includes providing an insulator and positioning the insulator between a vane support and a vane such that the insulator facilitates preventing hot gas migration into the vane, and such that during operation, hot gas is channeled from a high pressure side of the vane to a low pressure side of the vane. A vane assembly for a turbine rotor assembly is also provided. The vane assembly includes a vane support and an insulator including a projecting portion. The assembly also includes a vane. The insulator is coupled to the vane support such that the projecting portion is between the vane and a nozzle support strut to facilitate hot gas flow from a pressure side of the projecting portion to a suction side of the projecting portion.

Abstract: A high-speed air spindle including a spindle 1 supported by a first bearing 3 at the leading end side in the axial direction and a second bearing 2 at the rear end side, a driving air turbine 4 fixed in a spindle portion between the first bearing 3 and the second bearing 2, a speed-increasing air turbine 5 fixed in a spindle portion ahead of the first bearing 3, and an air passage 9 of an exhaust of compressed air supplied in the driving air turbine 4, flowing in the sequence of the first bearing 3 and the speed-increasing air turbine 5.

Abstract: A spindle device driven by driving fluid, having accurate rotation and superior quietness. The device includes a stator having at least one inlet for introducing the driving fluid, a rotor having at least one flange arranged outside of the stator and provided with nozzles for jetting the driving fluid, and a static-pressure fluid bearing for rotatably supporting the rotor with respect to the stator. The stator has a first inner path for conducting the driving fluid introduced from the inlet to the rotor and the rotor has a second inner path communicating with the first inner path of the stator for conducting the driving fluid to the nozzles. The driving fluid introduced from the inlet of the stator is jetted from the nozzles of the rotor through the first and second inner paths to rotate the rotor.

Abstract: A system for reducing oil usage from a sump in a gas turbine engine. Two sources of oil usage, which usage includes leakage and consumption, have been identified: (1) during idle, leakage of oil from an oil sump through seals and (2) during high-power operation, consumption of oil entrained in vent air exiting from the sump. At idle, the invention reduces pressure in the sump, to thereby increase airflow across the seals into the sump, to inhibit the oil leakage across the seals. At high power operation, the pressure reduction is terminated, but flow exiting the vent is artificially restricted.

Abstract: A pump for moving a liquid including a stator and a rotor which rotates to move at least one helical pumping member. The rotor in rotation is radially supported relative to the stator only by a layer of liquid maintained between the rotor and stator by rotor rotation.

Abstract: The invention relates to a deoiling device. It comprises a tube (46), a first bearing (16) and a second bearing (18), the first and second bearings being placed in an oil chamber (20) in which an oil fog is maintained by rotation of the bearings. A deoiler (30) is provided in one wall of the oil chamber. The deoiler centrifuges oil in suspension in air and allows a deoiled air flow to pass inside the tube. The tube (46) comprises a closing cap (48) fitted with one or several outlet orifices (50) in its upper part designed to evacuate air, and an oil drain orifice (52) in its lower part.

Abstract: A turbine blade outer air seal segment assembly has a first turbine blade outer air seal segment with a first end portion, a middle portion and a second end portion. The first turbine blade outer air seal segment is for connection with a second turbine blade outer air seal segment to form at least a part of a shroud of a turbine rotor. A first cooling passage is disposed within the first turbine blade outer air seal segment. The cooling passage extends from the first end portion to the second end portion and a land is disposed in at least one of the first or second end portions. The land represents a portion for receiving a mold ejection pin for a core forming the cooling passage.

Abstract: One embodiment of a transition-to-turbine seal (300) comprises a transition exit seal (302) adapted for fixed attachment to an exit rail (350) of a transition (109), and a stage-1 seal (340). The stage-1 seal (340) comprises an axial seal slot (348) comprising parallel walls (346, 347) adapted to slidingly engage a first male member (310) of the transition exit seal (302). The stage-1 seal (340) also comprises a radial seal slot (354) comprising parallel walls (351, 353) adapted to slidingly engage a plate (338) of a row 1 vane segment (330). The transition-to-turbine seal (300) thus provides both axial and radial freedom of movement. Materials and coatings for the transition exit seal (302) and the stage-1 seal (340) are selected to promote preferential wear of these components relative to wear of the surface of the row 1 vane segment (330). Wear of the exit rail (350) is reduced or eliminated due to the noted fixed attachment.

Abstract: A fluid flow machine has a main flow path, in which at least one row of blades (1) is arranged, and a shroud (2), which is embedded in a recess (3) of a component, with the component and the blades (1) being in relative rotational movement to each other. The assembly forming the shroud includes at least one internal chamber (7) which is suppliable with fluid from a source. The at least one internal chamber (7) is connected to the main flow path surrounding the blades (1) or to a cavity (9) surrounding the shroud (2) via at least one outlet (8) which is arranged on one side of the shroud (2). The shape of the outlet (8) and the shape of the outlet opening are such that a fluid barrier jet is generated at the outlet (8), which stops recirculation of fluid through the shroud cavity (9).

Abstract: A support and air mixer includes an inner annular member, an outer annular member shaped and positioned such that an annular air gap is formed between the inner annular member and the outer annular member, and a plurality of air mixing members, each air mixing member having a mixing passageway therethrough and each air mixing member having an inner portion connected to the inner annular member, an outer portion connected to the outer annular member, and first and second opposing side portions interconnecting the inner and outer portions and the inner and outer annular members such that the mixing passageway is in fluid communication with the annular air gap.

Abstract: In one embodiment, and by way of example only, a seal is provided for sealing a hollow shaft, where the hollow shaft has an inner surface that may be uneven due to shot peening. The seal includes an axially extending ring section having a first end, a second end, an inner surface, and a disk section disposed substantially perpendicular to the ring section inner surface between the ring section first and second ends. The seal conforms to the shaft inner surface to stop oil leakage.

Abstract: The invention relates to an inter-turbine casing (40) for a turbofan (2), comprising an outer ring (44), an inner ring (54), and an intermediate ring (52) between the inner ring and the outer ring, the inner (54) and intermediate (52) rings having respective openings (540, 520) for the passage of cooling air. The casing is distinguished in that it comprises at least one sealing device (80), arranged between the outer ring (44) and the intermediate ring (52), with a base (82), provided with at least one orifice (90) for the passage of cooling air, and a peripheral skirt (84) which is able to be compressed and expanded elastically, the base (82) bearing against the outer ring (44) and the peripheral skirt (84) bearing against the intermediate ring (52).

Abstract: The invention relates to a system of shaft sealing for a turbine engine. Carbon-ring seals placed on pressurized bearing compartments are adapted to operate on ceramic runners which are cooled by lubricating fluid. The runners are closed at one end so that fluid does not enter an interface between the runner and the seal. The seal is held in place in a cylindrical seal housing with an inwardly projecting seal retention wall. An internally cooled seal housing is provided having an enclosed annular cooling groove is formed in the wall. Fluid is circulated through the groove to provide cooling of the seal housing and the carbon-ring seal. The circulated fluid is provided from the same source as fluid that is circulated to lubricate bearings on the engine. However, a separately controlled fluid delivery system is employed so that a rate of flow of fluid to the seal housing can be specifically controlled.