Abstract: A seal assembly for a gas turbine engine includes a carbon seal and a seal plate. The seal plate has a contact face configured to slidably engage the carbon seal. The seal plate has a surface disposed on an opposing side of the seal plate from the contact face. The surface forms a portion of a single passage that extends an entire length of the seal plate. The continuous cooling provided by single passage along the seal plate allows for a more uniform temperature profile along the contact face of seal plate.

Abstract: A seal for use in a centrifugal pump, the pump having a stationary pump casing, a stationary plate and an axially adjustable side liner, is disclosed. The seal includes a base having an inner surface and an outer surface. A band portion extends from the base and a retainer member extends from the band portion. The retainer member is spaced apart from the base and oriented for positioning against a groove formed in the axially adjustable side plate liner of the centrifugal pump.

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

Abstract: This hydraulic machine comprises a wheel supported by a shaft (5), the wheel and the shaft being able to rotate about a vertical axis (X5) while a radial hydrostatic or hydrodynamic bearing (100) is formed between, on the one hand, a radial peripheral surface (52) of the shaft and, on the other hand, an internal radial surface (102) of a member (101) that is fixed relative to the vertical axis. The bearing (100) extends between two edges (121, 122) which, in normal operation, constitute regions for the removal of a film of water formed in the bearing. At least one cavity (130) is created in the fixed member (101) and opens onto its internal radial surface (102) near a first edge (122) of the bearing. The machine comprises means (131, 132, 133) for placing the cavity (130) in fluidic communication with a volume (V1) situated outside the bearing near the second edge (121) of the bearing (100).

Abstract: A system includes a brush seal segment. The brush seal segment includes a movable support including a head, an extension, and a seal surface, wherein the head is configured to mount in a chamber. The brush seal segment also includes a brush coupled to the movable support along the seal surface, wherein the seal surface consists essentially of the brush. The brush seal segment also includes a biasing element coupled to the movable support, wherein the biasing element is configured to bias the movable support from a first position to a second position to increase a brush clearance in a space between the brush and a rotor, and the movable support is configured to move from the second position to the first position to decrease the brush clearance in response to a fluid flow from the space to the chamber.

Abstract: A rotating element is associated with at least one bearing compartment that includes a bearing to support the rotating element. A seal resists leakage of lubricant outwardly of the bearing compartment and allows air to flow from a chamber across the seal and into the bearing compartment. The seal has a seal face facing a rotating face rotating with the rotating element. The seal is a non-contact seal. A gas turbine engine is also disclosed.

Abstract: There is provided a fuel pump (10) which includes an impeller (20) in a disk-like shape; a casing (18) comprised of a pump cover (14) and a pump body (16) that rotatably accommodate the impeller; and a motor section (70) that drives to rotate the impeller; wherein, on at least one of seal portions of the casing (18) and in its place facing to a series of recesses (20b,20c) of the impeller, a recessed shape (35,36) in a micron order is formed in expectation of a swelling amount of the series of recesses (20b,20c) of the impeller (20).

Abstract: A mechanical seal is disclosed having a rotatable sealing face and a stationary sealing face that are in opposed relation and arranged to be urged, into contact to form a seal. One of the sealing faces is mounted on a support assembly that includes a biasing device operative to move that sealing face into contact with the other sealing face. In one form of the invention, the biasing device includes one or more resilient members that in use are deformed to provide the biasing force. In a second form of the invention, the support assembly forms part of a fluid barrier of the seal and the biasing device is fluid impervious and forms part of the barrier. In a third form of the invention, the biasing device is exposed to fluid pressure in the chamber and the biasing force increases on increasing the fluid pressure in the chamber.

Abstract: A method of assembling a sealing assembly for use in a turbomachine includes providing a rotatable element that includes an end portion with a plurality of grooves partially extending circumferentially about a portion of an outer surface of the end portion of the rotatable element. The method also includes providing a stationary portion that includes an upper section and a lower section. The method further includes inserting at least a portion of the end portion of the rotatable element into the lower section. The method also includes coupling the upper section to the lower section, thereby defining a rotor shaft cavity. The end portion of the rotatable element at least partially extends through the rotor shaft cavity, thereby defining a clearance between the end portion of the rotatable element and the stationary portion.

Abstract: A gas turbine engine has a pair of components having a high-pressure chamber on one side, and a low pressure chamber on an opposed side. A three-sided seal has one side in sealing contact with each of said components. A third side is associated with a third component. At least one non-metallic wear surface is positioned between one of the three sides of the seal and its respective component.

Abstract: A bifurcation aerofoil having a leading edge portion and flanks where the leading edge portion is mounted to an inner wall of the bypass duct using a floating seal which permits circumferential movement of the leading edge. A cowl has a wall that provides the flanks of the aerofoil. On closing of the cowl into its flight position any contact between the flanks and the leading edge portion enables realignment of the leading edge portion to the inner wall of the bypass duct.

Abstract: An oil deflector includes a segment array extending radially from a sleeve portion defining a longitudinal axis and configured for mounting on a shaft. The segment array includes a plurality of segments arranged circumferentially relative to the longitudinal axis and defines at least one oil diverting feature configured to create a pressure differential proximate the segment array or across a surface of the segment array during rotation of the oil deflector about the longitudinal axis. The segment array may define an oil diverting feature configured as a radially tapered peripheral surface, an axially inclined annular surface, at least one slot inclined relative to an annular surface of the array, and/or a combination of these configured to divert oil axially and/or radially from the oil deflector during rotation by the shaft in use.

Abstract: A casing structure for a fluid flow machine, in particular for a gas turbine or an aircraft engine, including an outer casing wall and an inner casing wall, which annularly surround a flow channel of the fluid flow machine and are spaced apart in a radial direction with respect to the flow channel. At least one cavity is formed between the inner and outer casing walls. The cavity is axially divided into at least two regions which are separated from each other by an axial seal in such a way that different pressure conditions are created according to the axial position of these regions, which different pressure conditions correspond to the pressure conditions in the flow channel. A corresponding fluid flow machine such as, for example, an aircraft engine.

Abstract: A damping system for a gas turbine engine comprises a bearing mounted to a rotor shaft and a support connected to an outer race of the bearing. The support has a wall secured to a casing of the gas turbine engine at a connection portion. The wall has a first surface positioned against a surface of the casing with the first surface being in a non-parallel relation with the rotational axis of the rotor shaft. A cavity is defined in the first surface by a narrowing of a thickness of the wall. The cavity contains a damping fluid to dampen elastic deformation of the wall at the cavity resulting from axial oscillations of the rotor shaft. An abutment is provided to limit an amplitude of the elastic deformation of the wall.

Abstract: A fan structure includes a rotation module, a fixing shaft and an impeller, the rotation module comprises a coupling base, a bearing and a sealing member. The bearing comprises an axial hole, an outer ring wall and a through hole, a slot is recessed from the outer ring wall, the through hole communicates with the slot and the axial hole, and the slot is sealed by the sealing member to form an oil storage space. The fixing shaft penetrates the axial hole, and the through hole communicates with the axial hole and the oil storage space. When the rotation module rotates, lubricants in the oil storage space can flow from the through hole to the axial hole for lubricating the fixing shaft and the axial hole. When the rotation module stops, lubricants in the axial hole reflow to the oil storage space via the through hole to avoid loss.

Abstract: A steam turbine is provided having a relief groove which is arranged in the region of the equalizing piston and extends in the circumferential direction of the rotor. The relief groove, with regard to an inlet passage, is arranged in the axial upstream direction so that it is arranged on the rotor outside a region in which the steam flow enters the bladed flow path via the inlet passage. The relief groove, with regard to the first blade row, is arranged in a region in which the greatest thermal stresses can arise in the rotor. As an option, the relief groove has a cover for reducing vortex flows, and also devices for reducing heating of the groove or devices for active cooling. The steam turbine allows an increased number of risk-free running up and running down operations of the steam turbine with minimum detriment to the turbine performance.

Abstract: A seal structure for a gas turbine engine, the seal structure including first and second components located adjacent to each other and forming a barrier between high and low pressure zones. A seal cavity is defined in the first and second components, the seal cavity extending to either side of an elongated gap extending generally in a first direction between the first and second components. A seal member is positioned within the seal cavity and spans across the elongated gap. The seal member includes first and second side edges extending into each of the components in a second direction transverse to the first direction, and opposing longitudinal edges extending between the side edges generally parallel to the first direction. The side edges include a groove formed therein for effecting a reduction of gas flow around the seal member at the side edges.

Abstract: An example of a turbomachine seal includes, among other things, a sealing member configured to be influenced by both hydrostatic and hydrodynamic forces when providing a seal.

Abstract: In accordance with one embodiment of the present disclosure, a method may include installing a first seal around a motor shaft. The method may also include installing a second seal around the motor shaft, wherein the second seal and the first seal may form a hydrodynamic seal when the motor shaft rotates. The method may further include installing a spacer in-between the second seal and the first seal.

Abstract: A circumferential sealing arrangement is disclosed herein. The circumferential sealing arrangement includes a seal runner operable to be fixed to a structure for concurrent rotation with the structure about an axis. The circumferential sealing arrangement also includes a housing that encircles the seal runner or is encircled by the seal runner. The circumferential sealing arrangement also includes a primary seal element at least partially disposed in the housing. The primary seal element includes a first surface cooperating with a second surface of the seal runner to form a circumferential seal between the primary seal element and the seal runner. The circumferential sealing arrangement also includes a secondary seal element positioned between the housing and the primary seal element on a first side of the primary seal element along the axis of rotation. A second side of the primary seal element along the axis of rotation opposite the first side seals against the housing.

Abstract: An example housing of a cabin air compressor assembly includes a main body portion and a motor outlet duct extending radially from the main body portion. The motor outlet duct interfaces with the main body portion at an interface area. A ratio of a radius of the interface area to an inner diameter of the motor outlet duct is from 0.113 to 0.162.

Abstract: A rotating element is associated with at least one bearing compartment that includes a bearing to support the rotating element. A seal resists leakage of lubricant outwardly of the bearing compartment and allows air to flow from a chamber across the seal and into the bearing compartment. The seal has a seal face facing a rotating face rotating with the rotating element. The seal is a non-contact seal. A gas turbine engine is also disclosed.

Abstract: A pump and submersible solids processing arrangement includes a pump, having a suction inlet and discharge, and a submersible solids processing arrangement positioned in fluid communication with the suction inlet of the pump and being structured to macerate larger solids and matter that is entrained in a fluid to thereby reduce the size of the solids prior to entry of the fluid and solids into the inlet of the pump, the arrangement further including macerating members the speed and arrangement of which are selectively determinable or adjustable, and the arrangement further comprising an agitator arrangement for directing solids into the submersible solids processing arrangement.

Abstract: A support bearing arrangement comprises a gas turbine rotor shaft, a bearing stack, a bearing sleeve, and a support bearing. The bearing stack comprises a fore seal plate, and aft seal plate, and a bearing mount situated axially between the fore and aft seal plates. The bearing sleeve surrounds at least a portion of the rotor shaft, and is configured to form an insulating air gap between the rotor shaft and the bearing stack. The support bearing is mounted on the bearing mount to couple the gas turbine rotor shaft to a stationary structure, thereby centering and retaining the gas turbine rotor shaft.

Abstract: A seal support comprises a body, a seal carrier disposed circumferentially around an outer surface of the body, and a meshing ring extending axially forward of the seal carrier.

Abstract: A sealing assembly for use in a gas turbine engine having a disk arranged relative to an axis, the assembly including a circumferential groove defined in the disk and an annular wire seal positioned at least partially within the groove. The groove includes a first sidewall, a base portion adjoining the first sidewall, and a second sidewall adjoining the base portion opposite the first sidewall, wherein the second sidewall is angled in a range greater than 0° and less than 90° with respect to the axis.

Abstract: A compressor is disclosed having a shaft seal assembly and system that allows a high-pressure compressor to settle-out at a lower pressure level during shutdown. The seal assembly may be disposed about a portion of the shaft and define a blow-down seal chamber, the seal assembly including one or more gas seals in fluid communication with the blow-down seal chamber. A blow-down line is communicably coupled to the blow-down seal chamber to reference the blow-down seal chamber to a low pressure reference, such as a separate centrifugal compressor, or the like. Referencing the blow-down seal chamber to the low pressure reference reduces the required sealing pressure of the one or more gas seals. A valve may be disposed in the blow-down line and configured to regulate a flow of process gas leakage through the blow-down line.

Abstract: The present invention relates to a sealing arrangement for a flow machine. The sealing arrangement of the present invention is applicable for sealing bearing arrangements of centrifugal pumps, mixers, blowers etc. The present invention is especially applicable in sealing a bearing assembly including two angular contact ball bearings used in back-to-back configuration. The present invention relates especially to a baffle arranged between the bearing and the bearing housing, the baffle leaving a gap between itself and the inner bearing ring for the oil to flow from the bearing to the oil channel, and from the oil channel via a groove back to the oil chamber.

Abstract: An exemplary assembly includes a component of a turbocharger that includes a bore that extends between an inner, exhaust gas side of the component and an outer, ambient side of the component; a shaft that includes a pin portion and a head portion; a sleeve positioned on the pin portion of the shaft; and a bushing positioned over at least part of the sleeve and over at least part of the head portion of the shaft where the bushing seats the shaft and the sleeve in the bore. During operation of a turbocharger that includes such an assembly, the shaft, the sleeve and the bushing restrict flow of exhaust gas from the inner, exhaust gas side of the component to the outer, ambient side of the component. Various other exemplary devices, assemblies, methods, etc., are also disclosed.

Abstract: A waste water pump includes an impeller (10) having a suction port (12) with a sealing surface (14) which annularly surrounds this and which bears on a stationary seal (18). At least one groove (28) is formed in the sealing surface (14) and to both sides extends beyond a bearing-contact region of the stationary seal (18) on the sealing surface (14). The stationary seal (18) having a first end (30) in connection with an impeller side chamber (20) and an opposite second end (32) is in connection with the suction side of the impeller (10). The pump also includes means (34) for producing turbulences arranged in the impeller side chamber (20) adjacent the seal (18).

Abstract: A shaft sealing system and method are disclosed for a high or intermediate pressure turbine section having a rotating member including a shaft and a stationary member surrounding the rotating member and defining a steam flow path. The shaft sealing system comprises at least one seal disposed about each of a first end and a second end of the shaft; and a connection line for conducting steam from the first turbine section to a downstream portion of the turbine. The downstream portion of the turbine is one of a low pressure section and a condenser, and has a lower pressure than both of the first turbine section and ambient pressure conditions.

Abstract: A seal assembly forms a barrier between a compressor's interior and exterior regions. The seals assembly includes a primary seal stage and a secondary seal stage. The primary seal stage is formed of materials chosen to effectively block flow of gas through the seal assembly. The secondary seal stage is formed of materials chosen to survive a failure of the primary seal stage.

Abstract: A shaft sealing device and a rotary machine equipped therewith are provided with a sealing body configured by stacking a plurality of thin sealing pieces; and a low-pressure-side side sealing plate in which a plate surface facing the low-pressure side is pressed against an inner wall surface of the housing facing the direction of the axis by means of the pressure of a fluid applied from a high-pressure side to the low-pressure side. A protrusion for blocking a downward flow toward the inside of the low-pressure-side side sealing plate in the radial direction along the low-pressure side of the sealing body is formed on the inside of the low-pressure-side side sealing plate in the radial direction, and a communication path for guiding the downward flow blocked by means of the protrusion to a low-pressure-side region is formed on the housing.

Abstract: A multistage high-pressure pump according to the present invention includes a rotational shaft (1), impellers (3) secured to the rotational shaft, a casing (2) configured to house the impellers therein, a mechanical seal (20), a seal chamber (25) that houses the mechanical seal therein, an oil reservoir (30) configured to store oil therein, an oil supply line (26) providing fluid communication between the oil reservoir (30) and the seal chamber (25), an oil pump (31) configured to pressurize the oil from the oil reservoir (30) and supply the oil to the seal chamber (25), a pressure retaining mechanism (32, 34, 35) configured to retain pressure of the oil in the seal chamber (25), and an oil outlet line (27) for discharging the oil from the seal chamber (25). The pressure of the oil in the seal chamber (25) is higher than pressure of the fluid.

Abstract: In a sealing device which seals between an outside space between an outer side in the radial direction of an external diffuser which has a tubular shape and forms an exhaust channel through which combustion gas rotating a rotor of a gas turbine passes in the inner side in the radial direction and an outside member which is disposed outside the external diffuser with an interval between them in the radial direction, and the exhaust channel by an end of the external diffuser, a first seal plate group and a second seal plate group in which a plurality of seal plates, which extend to the outer side in the radial direction from the end of the tubular external diffuser and reach the outside member, are laminated in contact with each other, and a spacer which maintains the first seal plate group and the second seal plate group with an interval in an axial direction in which a rotational axis of the rotor extends are provided.

Abstract: Apparatus for sealing and purging a bearing region includes a bearing housing having at least one hole that allows a flow of air to flow through the at least one hole, and at least one bearing seal that allows the flow of air to flow through the at least one bearing seal, thereby creating a pressure difference across the bearing seal. The apparatus also includes an air directional device having at least a portion of the flow of air to flow adjacent to the air directional device, and a pair of components having a gap between the pair of components that allows the at least a portion of the flow of air to flow through the gap, thereby purging the gap.

Abstract: An inner wall surface of a low-pressure-side side plate opposite to a lateral surface of a thin plats is formed along a direction crossing an axial direction of a rotating shaft such that a gap between the inner wall surface and the thin plate gradually decreases from a radially inner side toward a radially outer side of the low-pressure-side side plate.

Abstract: A lamellar seal for sealing a shaft which rotates around an axis, especially in a gas turbine, includes a multiplicity of lamella (13) which are spaced one beneath the other, arranged in a concentric circle around the axis, and fixed in their position, wherein the lamellae (13) by their surfaces are oriented essentially parallel to the axis. The lamellar seal is improved by the fact that the lamellae (13) have formed-on structures (19, 20, 21) in each case for positioning and retaining the lamellae (13) in the lamellar seal (12), which include one or more laterally projecting support arms (19, 20, 21) which engage in complementarily formed recesses (25, 26) of the end plates (15, 16).

Abstract: The piston ring sealing points of a sealing apparatus between the rotor and the housing of a continuous-flow machine each have a piston ring, a cylindrical contact surface, which is directed radially inward, on the housing, as well as an axial stop on the rotor. In this case, the piston ring of the outer piston ring sealing point has a larger external radius and a smaller internal radius than the piston ring of the inner piston ring sealing point. At the same time, the outer piston ring sealing point has a smaller internal radius than the inner piston ring sealing point. Because of the V-shaped arrangement concept, there is no need for a steel ring, shrunk onto the rotor, between the piston ring sealing points.

Abstract: An induced draught fan, including: a motor, the motor including a shaft; a volute; and a wind wheel. The volute is provided with an air intake and an air outlet. The wind wheel is arranged inside the volute. The top of the volute is provided with a through-hole. The shaft of the motor passes through the through-hole and is connected to the wind wheel. A seal ring is arranged on the volute corresponding to the through-hole. An outer side of the seal ring is provided with an annular groove. The volute is embedded in the annular groove. The middle of the seal ring is provided with a center hole. The middle of the side wall of the center hole is provided with a ring-like convex edge. The shaft passes through the center hole and contacts with the ring-like convex edge.

Abstract: A first bore is formed in a liquid ring pump. A shaft is in the first bore. A second bore is formed in the pump and is axially inward of the first bore. A first and second seal are in the second bore and around the shaft. The second seal is axially outward of the first seal. The second seal is free of an abutment axially outward of it and abutting up against it.

Abstract: A seal assembly for use with a turbine having a rotor and at least one turbine blade facilitates the use of a wire seal with seal plate segments. The seal assembly includes a plurality of seal plate segments and a plurality of retainers disposed on a rotor flange on the rotor. A seal member is disposed between the retainers and the seal plate segments. The seal assembly includes at least one attachment member disposed through the rotor flange that limits radial displacement of the seal plate segments.

Abstract: A seal is formed of a material including a crosslinked fluoropolymer. The seal substantially prevents leaks in a high pressure pump.

Abstract: Embodiments of a gas turbine engine including a lift-off finger seal are provided, as are embodiments of a lift-off finger seal and embodiments of a method for the manufacture thereof. In one embodiment, the gas turbine engine includes an engine housing having low and high pressure cavities, a shaft rotatably mounted in the engine housing, and a lift-off finger seal. The lift-off finger seal includes an finger seal backing spring and an aerodynamic foil. The aerodynamic foil extends around the outer circumference of the shaft and is configured to expand radially outward in response to aerodynamic forces generated during rotation of the shaft. The finger seal backing spring resiliently biases the aerodynamic foil toward the shaft, deflects to accommodate the outward radial expansion of the aerodynamic foil, and forms an annular seal around the aerodynamic foil to impede pressurized airflow from the high to low pressure zone.

Abstract: The rotating machine includes a rotating shaft, a case surrounding the rotating shaft, the case being provided with a fluid storing chamber and formed with a housing section. The rotating machine further includes a bearing disposed in the housing section and supporting the rotating shaft, and a ring-like seal member disposed between the fluid storing chamber and the bearing for suppressing the fluid from flowing through a clearance between the rotating shaft and the case. The case is formed with a drain hole for making communication between atmosphere and a space surrounded by the seal member and the bearing within the case and discharging the fluid leaking from the fluid storing chamber and passing the seal member to enter the space, and an atmosphere introducing hole for introducing outside air into the space to keep the space at atmospheric pressure.

Abstract: Embodiments of the invention provide a pump with a housing including a pump chamber and an impeller positioned within the pump chamber. The pump also includes a socket with a wear plate, an inner ring, and an outer ring. The wear plate at least partially defines the pump chamber. The impeller is in contact with the wear plate. An outer surface of the outer ring is coupled to the housing. An inner surface of the outer ring receives a bearing. The inner ring receives a seal. A portion of the housing is molded over an end of the socket.

Abstract: A sealing device includes a housing rotatably accommodating a rotary shaft, guide parts extending along a radial direction and an axial direction of the rotary shaft, and arranged side-by-side in a circumferential direction of the rotary shaft, a partition part that is a partition between spaces between the guide parts and an outside space, a first seal part that is an annular protrusion, forming a first gap with respect to the rotary shaft or the partition part, and blocking a flow of fluid passing through the outside space, and a second seal part that is an annular protrusion extending in the radial direction, forming a second gap with respect to the rotary shaft or the housing, and blocking a flow of fluid that has passed through the spaces between guide parts and a flow of fluid that has passed through the first seal part.

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 brush ring seal device for installation within a packing case of a turbine includes: a brush seal carrier having a substantially ring-shaped body portion having a front face, a rear face, an inner circumferential groove, and an outer circumferential groove; a brush seal mounted within the inner circumferential groove of the brush seal carrier; and a ring-shaped spring mounted within the outer circumferential groove of the brush seal carrier. The rear face of the brush seal carrier is coated with an anti-friction coating, thereby allowing movement of the brush ring seal device within the packing case.

Abstract: A seal assembly that limits gas leakage from a hot gas path to one or more disc cavities in a turbine engine. The seal assembly includes a seal apparatus that limits gas leakage from the hot gas path to a respective one of the disc cavities. The seal apparatus comprises a plurality of blade members rotatable with a blade structure. The blade members are associated with the blade structure and extend toward adjacent stationary components. Each blade member includes a leading edge and a trailing edge, the leading edge of each blade member being located circumferentially in front of the blade member's corresponding trailing edge in a direction of rotation of the turbine rotor. The blade members are arranged such that a space having a component in a circumferential direction is defined between adjacent circumferentially spaced blade members.