Abstract: Enhanced abrasion resistance in well fluid wetted assemblies is described. The bearing set of the invention provides an enhanced abrasion resistance that is better capable of withstanding friction from solids in electric submersible pump (ESP) well production applications. The flutes, grooves, sectors and intersections of the invention provide improved fluid and solid flow through assembly components, which improves cooling while the assembly is in operation and reduces body wear, thereby increasing the lifespan of the ESP system.

Abstract: A bearing unit for a turbocharger, including a bearing housing extending in an axial direction and also including a bearing cartridge arranged within the bearing housing, wherein between the outer circumference of the bearing cartridge and the bearing housing there is formed an intermediate space with an oil film, and wherein the bearing housing has a supply bore formed for the supply of oil to the oil film. The bearing cartridge includes a rolling bearing, the outer cartridge ring of which is mounted in a freely rotatable manner in the oil film. A bearing unit for a turbocharger, the bearing cartridge of which includes a rolling bearing, the bearing outer ring of which is mounted in a freely rotatable manner in the oil film. By means of bearing units of such design, it is possible to ensure the secure mounting of a shaft even without a separate twist prevention device.

Abstract: A pump having a pump chamber and an impeller which rotates therein has an inlet leading into the pump chamber and an outlet leading out of the pump chamber, the pump having a pump motor having a rotor. The rotor and the impeller are connected to each other, the impeller being supported in an axial direction towards the inlet and an axial support being provided therefor against an axial bearing. In this instance, the axial bearing is located on a rotation axis of the rotor and includes a centrally supported concave bearing shell in which a convex-curved bearing projection of the impeller is in abutment.

Abstract: In a method of making a turbocharger housing surfaces of a sheet-metal shell which bound a gap towards the turbine wheel are measured, after the sheet-metal shell has been joined with a bearing flange provided for support of a turbine wheel, to generate measuring values. Subsequently, the bearing flange is machined in dependence on the measuring values for establishing a position of the turbine wheel in relation to the bearing flange and thus of the sheet-metal shell.

Abstract: A seal for sealing a space between a housing and a rotatable shaft disposed within the housing includes an annular, elastomeric seal body disposeable about the shaft. The body has a central axis, an outer portion disposeable within a housing recess, and an inner portion with a lip engageable with the shaft. At least a portion of the seal body is configured to bendingly deflect when fluid pressure exerted on the body exceeds a predetermined value such that at least a section of the body inner portion displaces radially outwardly to permit fluid flow between the shaft and the seal body. A rigid support member is disposed within the body outer portion so as to be located at least partially within the housing recess and is configured to reduce bending deflection of the body inner portion so as to prevent disengagement of the body from the recess.

Abstract: A seal for sealing a gap between adjacent first and second components, includes a first portion for attaching to the first component and a second portion extending at an angle from the first portion, the second portion having a top extending therealong that is flat in an uninstalled position, a thickened portion beneath the top and a hinge wherein the thickened portion is disposed between the hinge and an end of the top.

Abstract: An example gas turbine engine includes a turbine and first and second spools coaxial with one another. The first spool is arranged within the second spool and extends between forward and aft ends. The aft end extends axially beyond the second spool and supports the turbine. A housing is arranged downstream from the turbine. First and second bearings are mounted to the aft end of the first spool and supported by the housing portion.

Abstract: An example annular turbomachine seal includes an attachment portion, a first leg radially inward of the attachment portion, and a second leg radially inward of the attachment portion and configured to block flow from directly contacting an attachment associated with a bearing compartment of a turbomachine.

Abstract: An exhaust-gas turbocharger (1) having a compressor (2); a turbine (3); and a bearing housing (4) which has a lubricant device (5) for shaft bearings (6, 7), which lubricant device can be connected via a lubricant feed line (8) to an engine lubricant circuit. A lubricant storage vessel (9) is connected between the lubricant feed line (8) and the lubricant device (5) of the bearing housing (4).

Abstract: A gas turbine is provided including a rotor which includes a rotor portion of a fluid bearing for rotatably supporting the rotor, a radially outer stator portion, a radially inner stator portion including a stator portion of the fluid bearing, a compressor air passage extending between the radially outer stator portion and the radially inner stator portion, and an annular gap between the rotor and the radially inner stator portion partially forming an annular air passage in communication with the compressor air passage, wherein along a flow direction of air flowing within the annular air passage a radius of the air passage decreases in a first portion and then increases in a second portion. Further a method for operating a gas turbine is described.

Abstract: A fan assembly for a computing device is disclosed. The device can include an impeller having a number of blades and a motor for turning the blades. The motor can turn the blades via a magnetic interaction between the impeller and the motor. A fluid dynamic thrust bearing can be used to control a position of the impeller relative to the motor. In particular, the impeller can be configured to rotate around an axis and the thrust bearing can be used to control movement of the impeller in a direction aligned with the rotational axis. In one embodiment, the thrust bearing can be configured to stabilize the impeller when vibratory forces act upon the fan assembly. More particularly, parameters associated with the thrust bearing can be selected to counteract vibratory forces emitted by a speaker system.

Abstract: A protective coating for a surface exposed to hot gas flow comprises a thermal layer, a conducting layer and an abrasive layer. The thermal layer comprises alumina having a sufficient amount of impurities to lower the thermal layer thermal conductivity. The layer is formed from a powder having a thermal conductivity no more than 10 BTU in/hr ft2 ° F., and overlies the surface. The conducting layer overlies the thermal layer. The abrasive layer comprises abrasive particles bonded in a metal matrix that is electroplated onto the conducting layer.

Abstract: A cabin air compressor housing for a cabin air compressor assembly includes a compressor volute configured to direct a compressed flow to a compressor outlet. The cabin air compressor housing also includes a journal bearing support having a journal bearing bore. The cabin air compressor housing further includes an interior portion between the compressor volute and the journal bearing support. The interior portion includes a plurality of cooling airflow holes having a ratio of a diameter of the journal bearing bore to a diameter of one of the cooling airflow holes between 3.64 and 4.52.

Abstract: In a seal assembly which is inserted into a space, the space being defined by a pair of concave portions provided on side surfaces of transition piece outlet flanges, including: a seal body in which a seal portion, which contacts each of side surfaces of a downstream side of combustion gas flowing through the transition piece of side surfaces which face each other in each of the pair of concave portions, is formed, and an elastic body which presses the seal body toward the downstream side, wherein the seal body includes a seal plate and a side plate, and the elastic body includes a seal plate contacting portion and an elastic portion.

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

Abstract: The arrangement of the present invention is applied to a compressor which comprises a bearing hub housing a crankshaft and presenting at least a first and a second bearing portion, spaced apart by a circumferential recess. The crankshaft presents at least a first and a second support portion, spaced apart by a circumferential recess, which is offset from the circumferential recess of the bearing hub. At least one of the bearing portions and support portions has an axial extension superior to that required for radially bearing the crankshaft, the first and second bearing portions defining, with the first and second support portions, respectively, a first and a second radial bearing regions having the axial extensions required for a radial bearing for the crankshaft, presenting lower loss by viscous friction.

Abstract: A gas turbine engine rotor section includes a rotor body with a ledge extending axially from a location on the rotor body. The ledge defines a radially inner surface radially inwardly of the ledge, and a hub extends axially from the rotor, and beyond the ledge. The hub has a radially outer surface spaced from the ledge radially inner surface. A first distance is defined between the radially inner surface of the ledge and the radially outer surface of the hub. A knife edge seal has at least one pointed knife seal portion at a radially outer end. A radially inwardly extending arm portion extends from the seal, and an axially inwardly extending portion extends axially inwardly from the radially inwardly extending portion. The axially inwardly extending portion has a radially outer face and a radially inner face, which are spaced by a second distance. The second distance is less than the first distance.

Abstract: A segment for a knife edge seal includes an arcuate segment with a first end with a first end surface and a second end with a second end surface. The first end surface and the second end surface are complementary and overlapping when the first end surface and the second end surface interface with ends of adjacent segments.

Abstract: A blower includes a housing including an inlet and an outlet, a stationary component provided to the housing, an impeller positioned between the inlet of the housing and the stationary component, and a motor adapted to drive the impeller. The stationary component includes a tube portion structured to retain and align a pair of bearings that rotatably support a rotor to which the impeller is coupled. The tube portion includes a diameter in a side closest to the impeller that is sufficient size to accommodate adhesive to retain one of the bearings.

Abstract: An exemplary center housing rotating assembly includes a turbine wheel (260); a compressor wheel (240); a center housing (210) that includes a through bore (215), extending from a compressor end to a turbine end along a bore axis, and a recess (217), adjacent the bore, in a plane orthogonal to the bore axis; a bearing assembly (230) positioned in the bore that includes a keyway (233); and an anti-rotation component (280) seated in the recess and at least partially in the keyway to restrict rotation of the bearing assembly in the bore. Various other exemplary devices, systems, methods, etc., are also disclosed.

Abstract: A hermetic compressor includes: a crank shaft rotated by using an axial direction as a rotational axis; a stator rotating the crank shaft; a first bearing penetrated by the crank shaft and rotatably coupled to one side of the crank shaft based on the stator to support one side of the crank shaft when the crank shaft is rotated; a support part having one side provided at the stator and the other side disposed to be adjacent to the other side of the crank shaft, based on the stator; and a second bearing coupled to the other side of the support part and supporting the other side of the crank shaft.

Abstract: A pump includes a drive shaft linked to a motor. The drive shaft passes through a seal assembly before passing into the pump chamber. The seal includes an outer seal housing that accommodates a lip seal. A portion of the drive shaft that passes through the seal assembly is coated with PTFE to prolong the working life of the seal assembly.

Abstract: A method of increasing wear resistance of one or more part(s) of a rotating mechanism includes manufacturing the one or more part(s) with a portion thereof configured to be exposed to wear during fluid flow associated with the rotating mechanism having a dimension different from that of a desired dimension, applying a protective coating of an aluminum bronze alloy to the portion through welding deposition, and mechanically treating the protective coating. The method also includes applying one or more layer(s) of solid-alloy over the protective coating through electro-erosion deposition, and continuing the mechanical treatment of the protective coating and/or the one or more layer(s) of solid-alloy after the solid-alloy deposition to obtain the desired dimension of the portion.

Abstract: The propensity for gas and soot leakage around a shaft, which extends through a bore which connects volumes of differing pressures, e.g., a turbocharger turbine housing and the ambient air, is minimized with the addition of a pair of seal rings axially biased by a spring to provide a continuous gas and soot seal. The spring may bias the seal rings apart from each other or towards each other.

Abstract: A seal assembly for sealing a rotatable shaft in a gas turbine engine, wherein the shaft includes sections of greater shaft diameter located both forward and aft of the seal shaft coupling point is provided. The seal assembly includes a first semi-annular segment with a first end, a second end, and a plurality of seal teeth, where the first and second ends each include an overlap joint. The seal assembly also includes a second semi-annular segment with a first end, a second end, and a plurality of seal teeth, where the first and second ends each include an overlap joint. The first end of the second segment is coupled to the first end of the first segment, and the second end of the second segment is coupled to the second end of the first segment.

Abstract: Embodiments of a bi-axial compliant bearing assembly and methods of assembling the bi-axial compliant bearing assembly are disclosed. A bi-axial compliant bearing assembly employs a transition bearing race. The transition bearing race comprises a cylindrical surface. The cylindrical surface is configured to rotatably engage a rotational bearing element and to slidably engage the rotational bearing element along an axis. The transition bearing race also includes a spherically-compliant surface. The spherically-compliant surface is configured to engage a spherically-compliant element and to enable the spherically-compliant element to rotate transversely to the axis.

Abstract: A stator seal for a turbine assembly includes a seal base securable to a turbine stator and including an annular inner surface, and an abradable coating disposed on the annular inner surface. The abradable coating and the annular inner surface have a predefined cross-sectional profile including a transient operation section that facilitates axial expansion and a steady state operation section that facilitates a tighter clearance.

Abstract: A compressor is provided with a substantially tubular compressor casing, a substantially circular lid that is provided inside an inner periphery of the compressor casing so as to close off an end surface of the compressor casing, a space that is enclosed by the lid and an inner circumferential surface of the compressor casing so as to accommodate a blade, and seal member that is provided in a circumferential direction on the space side of an outer circumferential surface of the lid, wherein a slit part is provided on the lid, radially inside the outer circumferential surface, where the seal member is provided, so as to extend in the axial direction from the space side of the lid.

Abstract: A bearing arrangement for a turbocharger, including a bearing housing-which extends in an axial direction, an anti-friction bearing, situated within the bearing housing, having an outer bearing ring and a number of rolling bodies and an axially extending shaft which is rotatably mounted within the bearing housing. It is provided that the shaft includes a rolling body raceway for guiding the rolling bodies. Moreover, the invention relates to a turbocharger having such a bearing arrangement. A bearing arrangement of this type allows the secure mounting of a shaft in a turbocharger with simple assembly and low costs.

Abstract: An exhaust gas turbocharger (1) with a compressor (2) which has a compressor wheel (3) arranged in a compressor housing (4); with a turbine (5) which has a turbine wheel (6) arranged in a turbine housing (7); and with a bearing housing (8) which is arranged between the compressor housing (4) and turbine housing (7); and which has a bearing (9) for a rotor shaft (10) which bears the turbine wheel (6) and the compressor wheel (3), wherein the bearing (9) has at least one ceramic insert (11, 12) which is on the bearing housing side and is under compressive prestress, and at least one ceramic insert (11, 12) which is on the motor shaft side and is under tensile prestress.

Abstract: A stator arrangement of an electric machine, particularly a generator in a wind turbine is provided. The stator arrangement is radially surrounded by a rotatably mounted rotor arrangement. During normal operation the stator arrangement is non-rotatably connected to a stationary part of the generator. The stator arrangement may be released from the non-rotatable connection to the stationary part of the generator so as to be revolved relative to the stationary part of the generator. A method for positioning such a stator arrangement is also provided.

Abstract: A seal for a gas turbine engine and a gas turbine engine employing such a seal are disclosed. More specifically, the engine includes a knife edge seal which is better able to withstand the extremely high temperatures and mechanical loads to which gas turbine engine components are increasingly subjected. By moving the knife edge seal to the aft hub and cantilevering its angle off of vertical, thermal and mechanical loads are balanced and thus thermal mechanical fatigue life is improved while low cycle fatigue is maintained.

Abstract: A gas turbine engine has a turbine section and an air moving section upstream of the turbine section. A seal is between a static surface and a rotating surface in at least one of the turbine section and air moving section. The seal includes a seal shoe which is biased at least in part by a spring force, with the spring force created by cuts formed to provide a gap to allow arms associated with the seal to provide the spring force. The movement of the shoe is along a direction having at least a component parallel to an axis of rotation of the gas turbine engine. In addition, an axially moving non-contact seal is claimed.

Abstract: Bolt holes 16 are formed in a joint part 14 of a turbine housing 12, with flanged bolts 40 screwed in the bolt holes 16. A flange part 32 of a bearing housing 30 is sandwiched between bearing surfaces 44a of the flanged bolts 40 and an inner end face 14b of the joint part 14. A sealing ring 48 is interposed in an annular space s. Before the flanged bolts 40 are fastened, there is formed a height difference G equivalent to a compression allowance h for the sealing ring 48, between an outer end face 60a of the joint part 14 and a bolt receiving surface 32a of the flange part 32. The flanged bolts 40 are screwed into the bolt holes 16 until the bearing surfaces 44a make tight contact with the outer end face 60a so as to resiliently deform the sealing ring 48.

Abstract: A turbine bucket includes an airfoil portion; a platform at radially inner end of the airfoil portion; a shank portion extending radially-inwardly of the platform; and a mounting portion extending radially-inwardly of the shank portion. The shank portion and the mounting portion have at least one axially-extending seal-engaging surface formed as part of a separable, non-integral isolation element that isolates the bucket from forces caused by a near-flow-path seal engaging the at least one axially-extending seal-engaging surface.

Abstract: A turbocharger including a turbine wheel having a hub-to-tip ratio of no more than 60% and blades with a high turning angle, a turbine housing forming an inwardly spiraling primary-scroll passageway that significantly converges to produce highly accelerated airflow into the turbine at high circumferential angles, and a two-sided parallel compressor. The compressor and turbine each produce substantially no axial force, allowing the use of minimal axial thrust bearings. The bearing housing forms a shroud for the internal side of the compressor wheel.

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

Abstract: A combustor-turbine seal interface is provided for deployment within a gas turbine engine. In one embodiment, the combustor-turbine assembly a combustor, a turbine nozzle downstream of the combustor, and a first compliant dual seal assembly. The first compliant dual seal assembly includes a compliant seal wall sealingly coupled between the combustor and the turbine nozzle, a first compression seal sealingly disposed between the compliant seal wall and the turbine nozzle, and a first bearing seal generally defined by the compliant seal wall and the turbine nozzle. The first bearing seal is sealingly disposed in series with the first compression seal.

Abstract: Pump, in particular a canned motor pump, to deliver liquids in water carrying domestic appliances and such like, which comprises a stator, a rotor and a drive shaft non-rotatably coupled to an impeller disposed in a pump compartment which is rotatably arranged inside a motor casing via bearing means wherein seal means are fitted on a first face end of the motor casing to seal said casing off against the pump compartment, wherein the bearing and seal means arranged on the first face end of the motor casing are in the form of a seal-bearing combination which comprises an axial bushing section for sliding arrangement on the drive shaft, a radial closing section to cover up the motor casing and at least one flexible seal element formed to said axial bushing section and/or said radial closing section.

Abstract: A system includes a multi-stage turbine. The multi-stage turbine has an interstage seal extending axially between a first turbine stage and a second turbine stage. The interstage seal has an upper body that extends from an upstream seating arm to a downstream seating arm. The upstream and downstream seating arms are designed to constrain movement of the interstage seal along a radial direction of the multi-stage turbine. The interstage seal also has a lower body that extends from a seating end to a hook end. The seating end is designed to constrain movement of the interstage seal along the radial direction. The hook end has a protrusion that extends crosswise relative to a base of the lower body. The hook end is designed to constrain movement of the interstage seal along the radial direction and an axial direction of the multi-stage turbine.

Abstract: A diffuser seal for an aft end of a high pressure compressor of a gas turbine engine is disclosed. The diffuser seal includes a flow guide carrier coupled to the diffuser case. The flow guide carrier is also coupled to a static seal. The static seal engages a rotary seal and permits air flow through the static and rotary seals in the aft direction. The flow guide carrier is also coupled to a fairing and a fairing/hub support. The flow guide carrier supports the fairing in a spaced-apart position with respect to the rear hub so that air flowing through the static and rotary seals passes between a forward surface of the fairing and the rear hub. The fairing/hub support extends forward from the flow guide support and engages an aft surface of the fairing thereby limiting movement of the rear hub and fairing in the aft direction. This design helps to prevent parts or debris from piercing the rear hub and entering the high pressure turbine in the even of a fan blade-out or fan blade-off event.

Abstract: The propeller blade seal positioning gauge provides for precisely marking the position(s) of the circumferential seal(s) about the blade shank of a controllable pitch propeller prior to propeller reassembly. The gauge includes an elongate arm having a stop extending from one end normal thereto. The distal portion of the arm is inwardly offset toward the spanwise axis of the blade to place the distal portion of the arm adjacent the blade shank. One or more marker notches are formed in either or both edges of the arm, their locations being precisely determined according to the specific propeller type. The stop is placed upon the butt of the blade and the tip of an appropriate marker is placed in the appropriate notch of the gauge. The device is then rotated about the blade shank to mark a circumferential ring about the shank to indicate the precise position of the seal.

Abstract: A compressor having a stator vane assembly having an inner ring and a seal carrier secured thereto, the seal carrier having two opposite seal carrier end faces and the inner ring having two inner ring end faces which face said seal carrier end faces and are received between said seal carrier end faces with an axial gap therebetween, at least one clamping element bearing axially with a first clamping element end face against the inner ring and with a second clamping element end face against the seal carrier and being axially resiliently clamped between the inner ring and the seal carrier. A compressor with a clamping element for radial clamping is also provided.

Abstract: A bearing assembly that includes a first bearing, a second bearing, a spring and a sleeve. The spring applies a preload to each of the bearings, and the sleeve surrounds the spring and the bearings. The sleeve includes an end portion that extends axially beyond the first bearing. The end portion includes a step down in the outer diameter that defines a seat for an o-ring.

Abstract: Gas turbine engines and related systems involving blade outer air seals are provided. In this regard, a representative blade outer air seal segment for a set of rotatable blades includes: a blade arrival end; and a blade departure end; each of the blade arrival end and the blade departure end being angularly offset with respect to a longitudinal axis about which the blades rotate.

Abstract: In order to provide a wind turbine generator with a shaft and a bearing system which bearing system, e.g., using less material or using material which is relatively cheaper or which is not needed to have the same strength in comparison with some other solutions, there is disclosed a wind turbine generator with a bearing system including a lockable connection comprising a bearing surface and a support surface which surfaces are engaged when the lockable connection is locked and where forces from the shaft are transferred via the bearing and into the support through the bearing surface and wherein a support angle of the support surface, relatively to a shaft plane formed by rotating the shaft around a first axis, which first axis is perpendicular to the centre axis and which first axis is comprised in a vertical plane, is ranging from and including 5 degrees to and including 70 degrees.

Abstract: A thrust-bearing (1) disposed to face a thrust collar provided on a rotary shaft, including: grooves (5) formed at a bearing-surface (4b); a first-groove-group (6A) constituted by a plurality of first-spiral-grooves (6) formed at an inner circumferential side of the bearing-surface (4b); a second-groove-group (7A) constituted by a plurality of second-spiral-grooves (7) formed at an outer circumferential side more than the first-groove-group (6A) and wound in the same direction as the first-spiral-groove (6); and an annular-land-section (8) formed at the side, to which a fluid is drawn, among the inner circumferential more than the first-groove-group (6A) and the outer circumferential more than the second-groove-group (7A), wherein some of the first-spiral-grooves (6) of the first-groove-group (6A) and some of the second-spiral-grooves (7) of the second-groove-group (7A) are in communication with each other via a partial-communication-section (11), at least one side of which is in partial communication with th

Abstract: A gas turbine engine includes high and low pressure turbines. A mid turbine frame is arranged axially between the high and low pressure turbines. A bearing is operatively supported by a support structure. An inner case is secured to the support structure and includes a first conical member and a bearing support to which the bearing is mounted. The bearing support includes a second conical member that is secured to the first conical member at a joint. The first and second conical members are arranged radially inward of the joint.

Abstract: A turbine ring assembly for a gas turbine, the assembly having a complete ring forming a single piece of ceramic matrix composite material (CMC), a metal structure for supporting the CMC ring having metal annular supports between which the CMC ring is placed while allowing differential expansion at least in a radial direction between the CMC ring and the annular supports, an arrangement for centering the CMC ring, and at least one element for preventing turning of the CMC ring about its axis.

Abstract: A propeller shaft of a marine vessel is supported by bearing means within a stern tube or frame. The stern tube or frame has an aft end provided with a sealing assembly for sealing the propeller shaft. The sealing assembly and the stern tube or frame have at least one leakage monitor line for monitoring the condition of the sealing assembly. The at least one leakage monitor line is provided with a circumferentially extending channel section.