Abstract: A hydraulic seal is defined between a rotating member such as a turbocharger shaft and a stationary member such as part of a bearing housing of a turbocharger. The members define a projecting annular disc that is received in an annular channel that is filled with hydraulic sealing fluid such as oil. Rotation of the rotary member applies a centrifugal force to the fluid thereby ensuring that it is retained in the channel between walls thereof and the disc. This annulus of fluid provides a hydraulic seal around the shaft between the bearing housing and the compressor or turbine housing. The oil is delivered into the channel from a supply in the rotary member. One of the walls of the channel serves as a weir whereby when the channel has an excess supply of oil is overflows the wall and passes the drain.

Abstract: A seal assembly limits gas leakage from a hot gas path to one or more disc cavities in a gas turbine engine. The seal assembly includes a seal apparatus associated with a blade structure including a row of airfoils. The seal apparatus includes an annular inner shroud associated with adjacent stationary components, a wing member, and a first wing flange. The wing member extends axially from the blade structure toward the annular inner shroud. The first wing flange extends radially outwardly from the wing member toward the annular inner shroud. A plurality of regions including one or more recirculation zones are defined between the blade structure and the annular inner shroud that recirculate working gas therein back toward the hot gas path.

Abstract: An improved air-riding seal system for turbine engines is presented. The seal system includes a movable primary seal assembly, a stationary secondary seal assembly, and at least one structure to increase the stiffness of a thin film between the primary seal and a rotating component. The primary seal assembly includes an annular seal ring and an arcuate support arm. The annular seal ring has a cross section that is substantially L-shaped and a surface with a step face and a circumferential dam. The arcuate support arm has a tooth at one end adjacent to an outermost circumferential surface along the seal runner, which could include an optional notch. The tooth and outermost circumferential surface are separated by a gap. The secondary seal ring is disposed between and contacts the primary seal assembly and housing structure so as to form a bore seal and a face seal therewith.

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 cooling fan with oil-impregnated bearing includes a base portion, a bearing, a fan hub, and a coil assembly. The base portion has a forward extended bearing housing, into which the bearing is tightly fitted with a colloidal material applied between them. The fan hub is mounted on and around the bearing housing, and has a rearward extended rotary shaft extended through a centered shaft hole of the bearing. An oil receiving space is formed on a wall of the shaft hole at a predetermined position. The coil assembly is externally tightly fitted around the bearing housing with a colloidal material applied between them. With the colloidal material, the bearing and the coil assembly can be associated with the bearing housing without detriment to the effective porosity of the bearing and the dimensional precision of the bearing housing. The oil receiving space also prevents the lubricating oil from leaking out.

Abstract: A single-bearing fan structure includes a fan frame having a bearing cup with a bearing received therein, the bearing cup having a radially inward protruded lip portion formed at a first end to abut on a top of the bearing, and a groove internally formed at a second end; a blade hub having a rotary shaft fixedly connected thereto with a distal end of the rotary shaft inserted into the bearing; a retainer engaged with the groove; a first elastic element fitted around the rotary shaft and located between the blade hub and the bearing; and a second elastic element received in the bearing cup and located between the bearing and the retainer. The first and second elastic elements and the bearing respectively axially and radially support the blade hub, enabling the fan structure to operate stably and have extended service life.

Abstract: A high pressure first stage turbine and seal assembly are described. In one embodiment, a high pressure turbine section is provided. The turbine section includes at least one stage, at least one rotor and a bucket assembly. The bucket assembly includes a bucket and an attachment fixture. The stage has a high root reaction during operation. An intermediate space is between the bucket assembly and a stationary component of the turbine section. A seal is provided between the stationary member and the rotor to facilitate preventing leakage from the intermediate space toward an end of the stage. Steam balance holes are provided in the rotor or the bucket to facilitate feeding steam towards an end of the turbine stage.

Abstract: A shaft seal for sealing a gap between a shaft and a casing is provided. The shaft seal includes a plurality of sealing modules, at least one fluid supply and one fluid drain, and a first main seal on which a major partial pressure difference occurs. Conventional shaft seals of the above type require significant amounts of additional barrier fluid in regular intervals to ensure suitable pressure gradients. In the presently proposed shaft seal, the first main seal is designed as a radial double seal which is defined by two gas seals having respective rotating sealing surfaces and stationary sealing surfaces, the pair of sealing surfaces being opposite each other in a respective sealing plane. The sealing planes extend in a substantially radial manner relative to the shaft.

Abstract: A turbocharger compressor includes a compressor housing having a housing wall that includes a shroud that defines a central air channel and a compressor inlet in fluid communication with the central channel and an inlet duct. It also includes a compressor wheel configured to draw air into the compressor inlet from the inlet duct and create a main airflow in the central air channel axially toward a compressor outlet. The compressor also includes a bypass channel that extends between an opening in the main channel located between the compressor inlet and compressor outlet proximate the compressor blades and the compressor inlet. The compressor also includes a deflector that includes a deflector surface that is configured to direct a bypass airflow in the bypass channel, and flowing in a direction from the main channel toward the compressor inlet, into the compressor inlet axially and radially inwardly toward the compressor wheel.

Abstract: A rim cavity seal arrangement for a gas turbine engine, where the rim cavity is formed between two rotor disk stages with a stator vane assembly positioned between the rotor disks and extending into the rim cavity. A cover plate secured onto a side of the rotor disk includes a plurality of cooling air injectors directed to discharge cooling air into an annular groove formed on the underside of the vane endwall adjacent to the rotor disk to form an air cushion that seals the rim cavity from hot gas ingestion. The cover plate forms a cooling air supply passage with the rotor disk side to supply the injectors, and the cover plate includes at least one metering hole to meter the pressurized air into the injectors.

Abstract: A shaft seal of the rotating wheel shaft of a turbomachine includes a rotating wheel-side seal and a bearing-side seal between the bearing housing and the shaft. An oil outlet chamber is arranged between the rotating wheel-side seal and the bearing-side seal. The oil outlet chamber is delimited by a third seal between the bearing housing and the shaft, and a gas discharge chamber is arranged between the third seal and the rotating wheel-side seal. The construction is actively cooled by means of at least one splash oil bore in the region of the oil drain channel, as a result of which coking of the shaft seal can be prevented. The third seal separates the oil issuing from the oil outlet chamber from the gas issuing from the gas discharge chamber.

Abstract: The present application provides a variable steam seal system for use with a steam turbine. The variable steam seal system may include a seal steam header, a first pressure section, a first pressure seal positioned about the first pressure section, and a flow path through the first pressure seal and extending to the seal steam header. The first pressure seal may include a moveable seal packing ring for varying the flow path through the first pressure seal to the seal steam header.

Abstract: Providing a sealing mechanism provided with bellows-joints, the sealing mechanism being manufactured without surplus time and labor; thereby, the natural frequencies regarding the sealing mechanism surrounding a to-be-sealed shaft body are easily handled. Around a rotor shaft 26 of a steam turbine 10, between an outer turbine casing 12 and a gland 32, a sealing mechanism 40A is provided; the sealing mechanism is provided with an outer bellows-joint 46 and an inner bellows-joint 48, both the joints being arranged without mutual contact; the left and right ends of the outer bellows-joint 46 are gas-tightly connected to the outermost end periphery of the end flange 42 and the end flange 44, respectively; the left and right ends of the inner bellows-joint 48 are gas-tightly connected to the innermost end periphery of the end flange 42 and the end flange 44, respectively. Positioning both the bellows-joints can be easily performed.

Abstract: A turbocharger has a sealing arrangement between the turbocharger shaft and the bearing housing adjacent to the turbine and/or the compressor housings to restrict leaking of gas into the bearing housing. At least a pair of spaced sealing rings project from an annular surface of the bearing housing into corresponding annular recesses formed on the shaft. The trailing face of the second ring or the opposite surface of the recess has a plurality of radial grooves that define leak passages that serve to maintain a very small flow of gas from the turbine or compressor housing into the bearing housing. Alternatively there is a slot in the second ring to provide the leak passage. This ensures that there is a minimum gas flow so that a large pressure gradient is not applied across the second seal thereby avoiding wear, overheating and collapse of the ring.

Abstract: A reverse flow tolerant brush seal arrangement for restricting the transfer of a pressurized fluid between a first and a second chamber along a moving shaft. Opposing backing plates are provided to stiffen brush bristle alignment on the moving shaft. Differential pressure between the chambers is aided by spring biasing to seat axial movement of a sliding brush seal against one of the opposing backing plates for stiffening to maintain a design clearance with a shaft being sealed.

Abstract: A shaft seal for sealing a gap between a shaft and a casing is provided. The shaft seal includes a plurality of sealing modules, at least one fluid feed and at least one fluid outlet. The sealing modules include an outer main seal, and inner main seal and a fluid drain between the two. Conventional shaft seals of the above type require significant amounts of additional barrier fluid in regular intervals to ensure suitable pressure gradients. In the presently provided shaft seal, the inner seal is designed as a radial double seal which is defined by two gas seals having respective rotating sealing surfaces and stationary sealing surfaces, the pair of sealing surfaces being opposite each other in a sealing plane. The sealing planes extend from the shaft in a substantially radial manner.

Abstract: A steam turbine comprises a rotor with moving blades attached thereto; diaphragms which surround the rotor from an outer periphery side of the rotor; a casing which encloses the diaphragms and the rotor and has an upper half and a lower half clamped together through respective flanges; a displacement detector for measuring a difference d in thermal expansion in the rotor axis direction between the casing and the rotor; heating/cooling devices attached to the flanges respectively to heat and cool the flanges; and a controller which makes control so that the flanges are heated or cooled by the heating/cooling devices until a measured value obtained by the displacement detector reaches a preset value M or S in unsteady operation.

Abstract: A turbine engine utilizes an oil director to direct any leakage oil from a rear bearing compartment of the turbine engine toward a drain opening for an oil drain. The oil drain is formed in a heat shield located between the low pressure turbine and the exhaust nozzle. The oil drain directs the leakage oil to a benign area of the turbine engine.

Abstract: A fan includes a base and an impeller rotatably mounted on the base. The base protrudes a tube outwardly therefrom. The tube defines a receiving hole therein for receiving a bearing. The bearing defines a bearing hole therein. The impeller protrudes a shaft therefrom towards the base. The shaft is rotatably received in the bearing hole. The fan further includes a gasket located at a bottom of the bearing and clipped on a free end of the shaft. The gasket includes a first surface and an opposite second surface. The first surface is a smooth surface and facing directly the bottom surface of the bearing. The second surface is a rough surface relative to the first surface. At least one of the first surface and the second surface is provided with a mark to differentiate the rough second surface from the smooth first surface.

Abstract: A gas turbine engine is disclosed that includes a spool having a compressor section. An inlet case is arranged axially upstream from the compressor section. A gearbox is secured to the inlet case. The gearbox couples the spool and a fan. A sealing assembly is arranged between the inlet case and the gearbox to provide a sealed bearing compartment. The inlet case, gearbox and seal assembly provide a module. A fastening element removably secures the module to the spool. The gas turbine engine can be serviced by disconnecting the fastening element from the engine core. The gearbox and inlet case can be removed as a module from the engine core without disassembling the gearbox.

Abstract: Sealing apparatus and engine are provided. A sealing apparatus includes a first cover plate, a second cover plate spaced apart from the first cover plate, and a sealing element disposed between the first cover plate and the second cover plate and including at least two diaphragm members, wherein a first diaphragm member has a first stiffness and a second diaphragm member has a second stiffness that is different than the first stiffness. The sealing apparatus may be disposed in an engine.

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 dynamic sealing system between two coaxial rotary shafts respectively comprising an inner shaft and an outer shaft. Connected to the inner shaft, the system comprises a sectorized annular assembly of wipers that are movable under the effect of centrifugal force, and an annular receptacle for liquid arranged in the inside surface of the outer shaft.

Abstract: A system for regulating a cooling fluid within a turbomachine. The system may include a plurality of bypass chambers, wherein each of the plurality of bypass chambers allows for the cooling fluid to pass from the compressor section to the at least one wheelspace area. The system may also include a plurality of bypass plugs, wherein each of the plurality of bypass plugs is insertable into a bypass chamber opening on each of the plurality of bypass chambers.

Abstract: An integrated duct, baffle and knife edge seal arrangement employing the radially inner distal edge of the baffle for sealing the radially inner stator/rotor interface of an inter-stage cavity.

Abstract: The invention relates to the uses and combinations of elastomeric seals, elimination of joints between segments of a seal grid, introduction of labyrinth seal profiles, abradable or conformable vane coatings, and crushable vanes or vane edges to provide lower leakage, lower friction, lower operating temperatures, and higher efficiency within an Oscillating Vane Machine.

Abstract: In an industrial pump, a bearing provided in a pump main body rotatably supports both end sides of a rotating shaft to which an impeller is attached. A shaft seal apparatus is arranged in adjacent to the bearing. The shaft seal apparatus is cooled by a cooling water introduced from an external portion. A shaft seal case is fitted to an inner peripheral surface of a bracket accommodating the shaft seal apparatus in accordance with a shrink fitting. A cooling water is circulated in a boundary portion between the bracket and the shaft seal case. It is omitted a work for closing an opening portion of a cooling means for circulating the cooling water by welding.

Abstract: The present invention aims at providing a technique for providing a stepped structure separately to a rotating shaft in a later step of assembly for preventing oil leakage from a bearing box. To this end, the rotating machine of the present invention includes a rotating shaft having a rotating member, a bearing device including a rotating shaft insertion hole larger in diameter than the rotating shaft, an oil thrower provided between an outer circumferential portion of the rotating shaft insertion hole and the rotating shaft, and an additional ring attached to the rotating shaft between the oil thrower and the rotating shaft such as to protrude in a radial direction of the rotating shaft.

Abstract: A first seal member 21A according to a first embodiment of the present invention includes a double-structure bellows 22 in corrugated form, and vibration control means provided on the outside of the bellows 22 such as to cover part of the bellows 22. A flat portion 23 that is not in corrugated form is provided in part of the bellows 22. The vibration control means is provided in a circumferential direction on an outer surface of the flat portion 23, and made up of a ring-shaped rib 25 having a plurality of holes in a circumferential direction and weights 26 inserted in the holes provided in an outer wall of the rib 25. Natural frequency is adjusted by adjusting the number of weights 26, thereby preventing resonance between the natural frequency of the first seal member 21A and the rotational frequency of a rotor from occurring.

Abstract: A pump has a shaft, an impeller arranged on the shaft, and a labyrinth seal which is arranged between stationary and moving parts of the pump. A plurality of blades are arranged on the rotor and a labyrinth seal extends at least between the shaft and a rear portion of the blades. A gap in the labyrinth seal is designed such that liquid water can be actively carried away, with the labyrinth seal for this purpose being designed at least in places with a channel in the form of a spiral and/or a staircase. The invention also relates to a fuel cell system having such a pump.

Abstract: A flow machine (1) has an outer housing (2) with an inner housing (6), particularly a guide blade carrier, arranged therein and a rotor shaft (10) which is situated in the latter, a cover (4; 8) which is fastened to the outer housing (2) and separates an inlet pressure (p1) in the interior of the outer housing (2) from an ambient pressure (pu) outside the outer housing, and a compensating piston seal (22) for sealing an outlet pressure (p2) in a work space, particularly compression space (16), defined between the rotor shaft (10) and the inner housing (6) against the inlet pressure (p1) in a noncontacting manner. The compensating piston seal (22) is fastened to the cover (4; 8).

Abstract: A high pressure turbomachine includes a casing having an interior chamber, an opening into the interior chamber, and a generally annular wall section extending about the opening and having an outer circumferential surface. A closure device is engageable with the casing and includes a body having an inner circumferential overlap surface defining an opening. The closure body is configured to receive at least a portion of the casing annular wall section within the body opening such that the closure body overlap surface extends about the annular wall section outer surface so that the body substantially closes the casing opening. When the casing chamber contains high pressure fluid, the casing wall section expands radially outwardly such that the casing section outer surface pushes generally radially outwardly against the closure body overlap surface, the closure body being configured to either minimize or substantially prevent casing wall radial expansion.

Abstract: In the method, a support is provided presenting an annular base for a wiper, and the projecting portion of the wiper is built up by depositing successive layers on the base by performing the following steps: activating both a laser source connected to an optical head focused on a point of the surface of the top of the base and a source of powder that is connected to a spray nozzle, thereby forming a localized melt at said point, with the powder being injected into the melt, thereby forming a localized region of extra thickness; and aiming the optical head and the nozzle on another point adjacent to said region of extra thickness, and returning to the preceding step, until a layer has been formed over substantially the entire base.

Abstract: The present invention discloses structural improvement of the vertical submerged pump for chemical application. The present invention is focus on reducing the crystal lump generated from high speed etching process. Structural improvement includes a shaft seal device, a diffuser and an upper inner plate. The shaft seal device offer extra flow resistance to balance the differential pressure between the inner space and pump front casing, the function are prevents air bubbles be sucked into the pump, and reduces flow leakage from the front casing into inner space, also absorbs high-pressure back-flush to avoid liquid splash in dry surface of inner space of support column. The diffuser in the support column offer extra inducer function to guides the liquid from the inner space flowing out to the tank, so as to get a stable liquid level in the inner space, thereby largely reducing splashing of the liquid.

Abstract: A fuel pump includes a bearing element disposed in proximity to an impeller. The bearing element is configured to form a fuel seal with the impeller and to drain fuel leaked from the pump chamber back into the pump chamber. The bearing element minimizes leakage of fuel from the pump chamber into an engine coupled to the impeller. The fuel pump also includes redundant lip seals configured to provide redundant sealing relative to a shaft of the impeller within the fuel pump in order to minimize engine oil from entering the pump chamber and to minimize fuel from entering the engine. Integration of both the bearing element and the redundant lip seals as part of the fuel pump results in the fuel pump having a relatively compact size.

Abstract: Provided are a seal structure and a control method therefor that can improve sealing performance between a rotating portion and a fixed portion, smoothly start up a steam turbine, and suppress the temperature rise of the rotating portion even if the rotating portion is continuously rotated for a long period of time. A seal structure is configured such that seal fins 62 on a seal base-plate 61 side and corresponding breathable spacers 4b on a rotor 2a side are opposed to each other and breathable spacers 4a on the seal base-plate 61 side and corresponding seal fins 2a1 on the rotor 2a side are opposed to each other. The seal base-plate 61 is installed shiftably in a direction coming close to or moving away from the rotor 2a. If steam St has low pressure, the seal fins 62 and the corresponding breathable spacers 4b are not in contact with each other and the seal fins 2a1 and the corresponding breathable spacers 4a are not in contact with each other.

Abstract: The invention provides, in one aspect, a brush seal comprising brush seal bristles made up of component brush seal filaments. The component brush seal filaments comprise a polyether ketone comprising structural units derived from a diaryl ketone and a diphenolic compound and having a glass transition temperature in excess of 100° C. In a particular embodiment, the component brush seal filaments comprise PEEK. The novel brush seals provided by the present invention present a number of advantages over conventional non-metallic brush seals comprising KEVLAR filaments, such as enhanced friction characteristics and greater stability to fluid lubricants comprising groups reactive with the amide moieties present in aramid filaments such as KEVLAR.

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: Asymmetric loading within such machines as gas turbine engines can cause distortion of a casing surrounding a rotating assembly. Such distortion may cause rub and therefore inefficient energy usage and shorter operational life. By providing driver arms 112, 212, 312 which extend from radially extending links 113, 213 in a first or high pressure compressor inner casing 101, 201 to a second outer casing 108, compensation for asymmetric loading can be achieved. The casings 101, 201, 108, 208 are presented upon relatively stable bearing supports 102, 110 and therefore, reaction loads are compensated for in order to retain concentricity of the casing 101, 201.

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: With the multi-stage centrifugal pump assembly, the connection between the motor shaft (7) and the pump shaft (9) is effected by way of a thread (26, 27), which joins the fits (31, 34) lying therebehind, between a pocket hole bore (24) in the pump-side end of the motor shaft (7) and the motor-side end of the pump shaft (9). Thereby, a transition fit (32) is provided in the region of the bearing (11), and a press fit 34 in the free region therebehind.

Abstract: An axial face seal (13), which seals a pump housing in the region of the pump shaft (12), is constructed in an axially compact manner. Spring holders (24, 25), which transmit the required pressing force of a compression spring (23), are connected to one another with a positive fit in a rotation direction, and hold a rotating axial face seal ring (19) in a rotationally fixed manner to the pump shaft (12). The spring holders (24, 25) are compact and enclose an abutment ring (33) for pump impellers as well as the compression spring (23). A motor-side spring (24) engages over the rotating axial face seal ring (19), by which an axially extremely short constructional length is achieved.

Abstract: A multi-stage centrifugal pump assembly which is manufactured in the same construction type with cast components on the one hand, and with a stainless steel lining formed of sheet metal on the other hand, includes a bearing carrier (13) which is designed and suitable for the connection of a cast housing component (12) as well as for receiving a sheet metal lining made of stainless steel.

Abstract: A fan assembly for creating an air current includes a nozzle mounted on a base. The base comprises an outer casing, an impeller housing located within the outer casing, the impeller housing having an air inlet and an air outlet, an impeller located within the impeller housing and a motor for driving the impeller to create an air flow through the impeller housing. The nozzle includes an interior passage for receiving the air flow from the air outlet of the impeller housing and a mouth through which the air flow is emitted from the fan assembly. A flexible sealing member is located between the outer casing and the impeller housing.

Abstract: A rotor mechanism of a centrifugal compressor connectable to a power output device and configured to block leakage of lubricants and to recycle lubricants to an oil sump is provided, which includes a rotary shaft with a rolling bearing and a screw nut, a bearing housing for receiving the rolling bearing, and a bearing plate connected to the bearing housing. The screw nut has a surface provided with an oil throw seal, and the bearing housing. As the bearing plate is provided with an oil channel in contact with the oil-returning hole and either one of the bearing housing and the bearing plate is provided with a first labyrinth seal in contact with the screw nut, lubricants leaking out of the rolling bearing is allowed to go to the oil sump via the oil channel and oil-returning hole. The oil slinger thus blocks the lubricants from leaking out of the first labyrinth seal.

Abstract: A rotary machine and a method of assembling a rotary machine having a casing extending at least partially around a rotor are provided. The method includes providing a diaphragm patch ring. The method also includes assembling a diaphragm assembly by configuring a diaphragm bore portion to receive the diaphragm patch ring and forming a diaphragm patch member sub-assembly by coupling the diaphragm patch ring to the configured diaphragm bore portion, such that the diaphragm bore portion defines at least one dowel passage and at least one bolt passage. The method further includes inserting at least one dowel generally radially into the at least one dowel passage, inserting at least one fastening bolt generally radially into the at least one bolt passage to secure the diaphragm patch ring to the diaphragm bore portion, and positioning the diaphragm assembly in a gap formed by the casing and the rotor.

Abstract: A turbomachine comprises a housing (71) defining a bearing cavity (71) a and a turbine chamber (77a) separated by a first wall. A heat shield (72) is disposed between the first wall and the turbine wheel (77), a heat shield cavity (78) being defined between the first wall and the heat shield (72). The shaft (81) extends through a passage (85) defined at least in part by a first aperture (86) in said wall and a second aperture (87) in the heat shield (72). A first seal (88) is provide between the shaft (81) and said first aperture (86). The housing defines a first gas channel (79) communicating with the heat shield cavity (78) for connection to a pressure source for raising pressure within the heat shield cavity (78). A second channel (92) is provided between the heat shield cavity (78) and said passage (85), the second channel opening to said passage (85) on the opposite side of said first seal (88) to said bearing assembly (82).

Abstract: A turbocharger has a turbocharger housing and a through opening for a shaft. The shaft is pivotally supported in the housing by way of a bearing arrangement. Lubricating oil is supplied for lubricating the bearings. A section of the shaft is provided on the outside of at least one bearing, the section forming a gap together with the housing. The gap is configured as a lubricating oil regulator in order to at least reduce a passage of lubricating oil from the sides of the bearing.

Abstract: The present invention provides an apparatus and method for rotationally controlling a bearing assembly using a geared coupling system in combination with a supercharger including an input shaft. Generally, the geared coupling system includes a bearing assembly rotatably supporting a high speed shaft associated with an impeller, the bearing assembly including at least one inner bearing and at least one outer bearing; a drive gear associated with the input shaft and including a plurality of engaging members; and a geared coupler extending from a towards a plurality of engaging members adapted for engagement with the low speed gear, the geared coupler presenting an inner surface for receiving said inner bearing and an outer surface for receiving said outer bearing.

Abstract: Systems, methods and apparatus for controlling gas leakage in a turbine are provided. A plurality of seals may be provided in series, where each of the plurality of seals may be operable to reduce gas backflow from an inlet of a turbine component. Further, one or more channels may be provided that are operable to direct at least a portion of the gas backflow from respective points within the plurality of seals to corresponding points within a gas flow path of the turbine. The at least a portion of the gas backflow may be directed to the points within the gas flow path through the one or more channels. Additionally, the diameters of the plurality of seals may be optimized to at least partially balance the net thrust generated by the gas flow path of the turbine.