Bearing, Seal, Or Liner Between Runner Portion And Static Part Patents (Class 415/170.1)
  • Patent number: 10132182
    Abstract: A platform includes a platform body. The platform body has an airfoil support surface, an axially extending base surface opposite the airfoil support surface, and a leading edge. The leading edge includes an upstream extending flange with a raised portion and a trough portion downstream of and radially inward from the raised portion. The raised portion and the trough portion are for holding a vortex of fluid flow. The upstream extending flange includes a converging surface connecting the upstream extending flange to the base surface. The converging surface converges in a direction toward the axially extending base surface and is at an angle relative to the base surface.
    Type: Grant
    Filed: November 10, 2015
    Date of Patent: November 20, 2018
    Inventors: Andrew J. Aggarwala, Russell J. Bergman
  • Patent number: 10107294
    Abstract: The present invention relates to a coreless donut-type fan, and more particularly, to a coreless donut-type motor fan for ventilation and cooling, in which a rotating force is generated by wings themselves, without a separate rotational power such as a motor provided in a central portion thereof, and a through hole is formed in the central portion thereof to prevent a “wind barrier” phenomenon during rotation at a high speed, thereby maintaining smooth air flow, minimizing power consumption, in particular, preventing rotational noise due to induction of smooth rotation, and improving rotational efficiency.
    Type: Grant
    Filed: May 14, 2015
    Date of Patent: October 23, 2018
    Inventor: Suk Ho Jang
  • Patent number: 10094232
    Abstract: Aspects of the disclosure are directed to a seal comprising: a shoe, and at least one beam coupled to the shoe, wherein the seal includes a single crystal material with a predetermined crystalline orientation. Aspects of the disclosure are directed to a method for designing a seal, comprising: obtaining a requirement associated with at least one of: a geometrical profile of the seal, a temperature range over which the seal is to operate, a natural frequency associated with the seal, or a range of deflection associated with the seal, selecting a crystalline orientation for a single crystal material of the seal based on the requirement, and fabricating the seal based on the selected crystalline orientation.
    Type: Grant
    Filed: August 13, 2015
    Date of Patent: October 9, 2018
    Assignee: United Technologies Corporation
    Inventors: Michael G. McCaffrey, Eric A. Hudson
  • Patent number: 10053998
    Abstract: A gas turbine engine assembly includes a first module, a second module rotatable about a center line of the gas turbine engine and fluidly coupled with the first module, and a multi-purpose seal support. The multi-purpose seal support includes an aft end secured to the first module, and a forward end disposed proximate the second module. The forward end has a discourager portion, a seal portion, and a meshing portion.
    Type: Grant
    Filed: December 23, 2013
    Date of Patent: August 21, 2018
    Assignee: United Technologies Corporation
    Inventors: Tuan David Vo, Conway Chuong, Matthew Budnick, Jonathan Ariel Scott
  • Patent number: 10012111
    Abstract: A gas turbine, including: axially adjacent first and second components each having a gas path facing surface within an engine casing, inter-component cavity located between first and second components on the gas path outboard side, an axial-restrictor within the inter component cavity for restricting movement of the first or second component relative to at least one other first and second component or engine casing, wherein the axial-restrictor is radially located in the engine casing or other first and second component and includes a radially facing surface; a retaining element, including a body having circumferential length extending around the gas turbine engine and axial length extending between axially adjacent first and second components when in use; an obstructing portion between the radially facing surface of the axial-restrictor and opposing second radial surface of the other first or second component or engine casing to restrict radial movement of in use axial-restrictor.
    Type: Grant
    Filed: September 3, 2015
    Date of Patent: July 3, 2018
    Assignee: ROLLS-ROYCE plc
    Inventors: Andrew James Hurst, Mark John Simms
  • Patent number: 10012097
    Abstract: A nozzle sector of an aircraft turbo-machine, including a hooking member (64) having a projection (70, 70a, 70b) radially extending towards the outside of the sector, a recess (72) being provided through at least one part of a distal end of the projection (70, 70a, 70b), the recess (72) being configured to accommodate a shoulder member (74) forming a stop for a surface of an adjacent sector (26).
    Type: Grant
    Filed: February 19, 2014
    Date of Patent: July 3, 2018
    Assignee: SNECMA
    Inventors: Sébastien Jean Laurent Prestel, Denis Aydin, Rémi Blanc, Hélène Condat, Patrice Jean-Marc Rosset
  • Patent number: 9982685
    Abstract: A turbocharger compressor cover (114) including an inner shroud contour (122) configured to receive a compressor wheel (118) having a plurality of blades (140). Each blade (140) includes a leading edge (142), a contour edge (144), and a trailing edge (146). An inlet passage (124) leads to the inner shroud contour (122) and a circumferential groove (130) is formed around the inlet passage (124). The groove (130) includes a trailing edge (136) that is aligned with the outboard end (148) of the leading edge (142) of the blades. The compressor cover (114) includes an edge relief (138) formed along the groove trailing edge (136), such as a 45 degree chamfer. The circumferential groove (130) has a width and a depth, wherein the width and depth are approximately equal. The chamfer intersects the groove (130) approximately half the depth from the bottom of the groove (130).
    Type: Grant
    Filed: July 11, 2013
    Date of Patent: May 29, 2018
    Assignee: BorgWarner Inc.
    Inventor: Prasanth Vengala
  • Patent number: 9982539
    Abstract: Turbomachines having guide ducts are disclosed. One disclosed example turbomachine includes a rotor rotatable about an axis of rotation and having rotor blade ducts, a housing having housing ducts to allow the inflow or outflow of working medium and guide blade ducts fixed in the housing, where the rotor blade ducts are in fluid communication with the housing ducts via the guide blade ducts.
    Type: Grant
    Filed: April 30, 2014
    Date of Patent: May 29, 2018
    Assignee: DUERR CYPLAN LTD.
    Inventor: Frank Eckert
  • Patent number: 9951640
    Abstract: A structure providing compliance and sealing between ceramic or ceramic composite (CMC) part and a metallic part has an interface component for centering the CMC part in the metallic part, thus reducing thermal stress motion of the CMC component. In gas turbine engine applications, the structure comprises a CMC blade track inserted in a clip placed within a metallic hanger. The clip provides for radial compliance and secures controlled leakage of cooling air required to ensure that acceptable temperatures are maintained for the metallic structures. A washer is positioned adjacent to the clip provide for axial orientation of the blade track.
    Type: Grant
    Filed: December 27, 2013
    Date of Patent: April 24, 2018
    Assignee: Rolls-Royce Corporation
    Inventors: William I. Westphal, Clayton C. Smith
  • Patent number: 9915161
    Abstract: A process gas compressor/gas turbine section including a process gas compressor and a gas turbine which is coupled to the shaft of the process gas compressor in order to drive said compressor is provided. The process gas compressor is designed to compress combustible process gas and is equipped to seal the process gas compressor inner chamber from the atmosphere using a shaft seal which can be sealed with a seal gas and which has at least one leakage line. The leakage line can conduct leakage gas away from the shaft seal and is connected to the air inlet of the gas turbine such that the leakage gas together with the inlet air at the air inlet can be conducted into the gas turbine during the operation of the process gas compressor/gas turbine section.
    Type: Grant
    Filed: September 25, 2013
    Date of Patent: March 13, 2018
    Inventor: Henk Blekkenhorst
  • Patent number: 9850775
    Abstract: An integrated shroud structure surrounds a circumferential array of stator vanes and a circumferential array of rotor blades of a gas turbine engine. The shroud structure includes a plurality of vane shroud segments and a plurality of blade shroud segments. The blade shroud segments integrally extend downstream from the vane shroud segments and each pair of circumferentially adjacent blade shroud segments defines an inter-segment gap. At least one slot extends axially from a location downstream of the vane shroud segments to an aft end of the blade shroud segment. The inter-segment gaps and slots are sealed by a sealing band mounted around the full circumference of the integrated shroud structure.
    Type: Grant
    Filed: October 31, 2016
    Date of Patent: December 26, 2017
    Inventors: John Pietrobon, Remy Synnott
  • Patent number: 9835049
    Abstract: A distributor of a turbomachine configured to be mounted in a housing, including: a plurality of segments; a plurality of anti-rotation pins, mounted both on a segment of the distributor and on the housing; and a thermal protection sheet, including at least one axial tab configured to radially abut against an inner face of a first anti-rotation pin, and at least one radial tab configured to axially abut against an upstream face of a second anti-rotation pin.
    Type: Grant
    Filed: September 9, 2013
    Date of Patent: December 5, 2017
    Assignee: SNECMA
    Inventor: Julien Arnould
  • Patent number: 9835040
    Abstract: A turbomachine is described, which includes an annular space seal for at least reducing a fluid exchange between an annular space, through which a main stream flows, and at least one cavity situated radially on the inside and/or radially on the outside of the annular space, the annular space seal having a plurality of sheet-like elastic elements, which are oriented in the radial direction of the turbomachine and in the flow direction of a main stream flowing through the particular guide blade row, and thereby acting as a protective device for the rotor and/or stator during a relative axial displacement with respect to the stator in addition to providing an improved cavity coverage.
    Type: Grant
    Filed: October 7, 2014
    Date of Patent: December 5, 2017
    Assignee: MTU Aero Engines AG
    Inventor: Guenter Ramm
  • Patent number: 9822657
    Abstract: The aircraft-engine gas turbine includes an outer sealing ring for sealing an array of rotor blades that can be attached to a housing by a clamping mechanism (80) in a friction fit, and a plurality of ring segments (20i, 20i+1), wherein a free axial path length (af) of a sealing ring segment counter to the direction of through-flow is at least as large as an axial engagement (a1) of a rotation locking member (10) of the outer sealing ring (af?a1), which is free of form fit counter to the direction of through-flow, and/or an axial overhang (a2) of a radial mounting rail (23) of the outer sealing ring (af?a2), and/or an axial offset (a3, a4) of a sealing fin (31, 41); and/or a quotient of a specific clearance sum of the outer sealing ring attached to the housing in a friction fit.
    Type: Grant
    Filed: December 29, 2014
    Date of Patent: November 21, 2017
    Inventors: Walter Gieg, Petra Kufner, Rudolf Stanka
  • Patent number: 9631557
    Abstract: A sealing device for a nozzle of a turbomachine turbine including a turbine rotor. The turbine nozzle includes at least one inner annular platform. The turbine rotor includes a downstream spoiler disposed substantially axially. The sealing device includes at least one sealing sheet disposed, radially, between the inner face of the inner platform and the downstream spoiler of the rotor of the turbine so as to form an overlap clearance.
    Type: Grant
    Filed: May 4, 2012
    Date of Patent: April 25, 2017
    Assignee: SNECMA
    Inventors: Florent Pierre Antoine Luneau, Patrick Joseph Marie Girard, Sebastien Jean Laurent Prestel, Jean-Luc Soupizon
  • Patent number: 9605684
    Abstract: The invention relates to a pump for pumping contaminated liquid comprising solid matter, the pump comprising a hydraulic unit (2), a drive unit (3), and a sealing unit (4), the hydraulic unit having a pump chamber (5) and an impeller (8) that is suspended in a drive shaft (9), said impeller and said drive shaft forming a rotatable unit, the sealing unit comprising a seal housing cover (15) that delimits said pump chamber (5) and that forms a seat for a drive shaft sealing assembly (16), the seal housing cover (15) comprising a first gap-delimiting part (20) and the rotatable unit comprising a second gap-delimiting part (21), which jointly define an axially extending gap (22) situated in the pump chamber. The pump is characterized in that, in each arbitrary radially extending plane taken through said gap (22), the first gap-delimiting part (20) has a broken circular outer gap-delimiting surface (23) at the same time as the second gap-delimiting part (21) has a broken circular inner gap-delimiting surface (24).
    Type: Grant
    Filed: October 4, 2012
    Date of Patent: March 28, 2017
    Inventor: Patrik Andersson
  • Patent number: 9581041
    Abstract: The disclosure relates to a high temperature mechanical system, such as a gas turbine engine, including a first coating deposited on a first substrate and a second coating deposited on a second substrate. The first coating includes a first bond layer, a second bond layer, and a first ceramic outer layer, wherein the second bond layer is between the first bond layer and first ceramic outer layer. The second coating includes a third bond layer deposited on the substrate and a second ceramic outer layer deposited on the third bond layer. The second coating is configured to abrade the first coating, e.g., during operation of the high temperature mechanical system.
    Type: Grant
    Filed: February 9, 2011
    Date of Patent: February 28, 2017
    Assignee: Rolls-Royce Corporation
    Inventors: Raymond J. Sinatra, Jesse S. Daugherty, Marvin Alexander
  • Patent number: 9566654
    Abstract: An electrical discharge machining tool of a ring sector for an aircraft turbomachine is provided. The ring sector includes an abradable member and a support element to which the abradable member is fixed; and one or more gripping holes opening on a radially outer surface of a central body of the support element. The machining tool includes at least two machining sets chosen from groove, notch, opening, length-cutting, or abradable element electro-machining sets. The machining tool also has a gripping device for the ring sector by the gripping holes. The gripping device is configured to move the ring sector from one of the electro-machining sets to another of the electro-machining sets.
    Type: Grant
    Filed: December 11, 2014
    Date of Patent: February 14, 2017
    Assignee: SNECMA
    Inventors: Bruno Giardini, Antoine Marty, Xi Tian, Julien Arnould, Etienne Canelle, Frederic Hascoet, Matthieu Lebastard
  • Patent number: 9551354
    Abstract: A regenerative fluid machine having guide vanes on a flow channel wall is disclosed. The regenerative fluid machine includes a circular plate-shaped impeller having a plurality of vanes radially formed on an outer circumference thereof at regular intervals, casings in which the impeller is housed, and flow channels, each of which has a suction hole and a discharge hole in opposite ends thereof, and which are circumferentially disposed within the casings so as to face the vanes. The plurality of guide vanes having an inclined angle (?) with respect to a radial direction protrude from the flow channel wall in a rotational direction of the impeller so that a relative inflow angle (?) of the fluid introduced into the impeller grooves is increased and thus an absolute inflow angle (?) is decreased.
    Type: Grant
    Filed: May 9, 2012
    Date of Patent: January 24, 2017
    Inventors: Kyoung Yong Lee, Young Seok Choi
  • Patent number: 9422938
    Abstract: A centrifugal pump impeller includes front and back shrouds and a plurality of pumping vanes therebetween, each pumping vane having a leading edge in the region of an impeller inlet and a trailing edge, the front shroud has an arcuate inner face in the region of the impeller inlet, the arcuate inner face having a radius of curvature (Rs) in the range from 0.05 to 0.16 of the outer diameter of the impeller (D2) The back shroud includes an inner main face and a nose having a curved profile with a nose apex in the region of the central axis which extends towards the front shroud, there being a curved transition region between the inner main face and the nose. Fr is the radius of curvature of the transition region and the ratio Fr/D2 is from 0.32 to 0.65. Other ratios of various dimensions of the impeller are also described.
    Type: Grant
    Filed: April 10, 2015
    Date of Patent: August 23, 2016
    Assignee: Weir Minerals Australia Ltd.
    Inventors: Kevin Edward Burgess, Wen-Jie Liu, Luis Moscoso Lavagna
  • Patent number: 9394912
    Abstract: A combined axle structure of a stator assembly for a radiator fan, the radiator fan having a pedestal, a stator assembly a rotor blade unit and a reverse axle. The combined axle structure includes a cup-like metal bearing block having bottom and annular walls, an axle socket, and a reverse axle having a bottom end and a reverse pin joint end protruded upwards. The pin joint end is used for alignment and assembly of the sleeving set at the hub center of the rotor blade unit. The bottom end of the reverse axle is tightly inserted and located into the axle socket, the bottom of the metal bearing block is tightly embedded and located onto the embedded locator set at the center of the stator assembly face of the pedestal, and the metal bearing block is located onto the insulated frame via the top end of the annular wall.
    Type: Grant
    Filed: December 4, 2013
    Date of Patent: July 19, 2016
    Inventors: Liang-Sheng Chang, Tien-Chin Wu, Sheng-Chi Lei
  • Patent number: 9382806
    Abstract: Intermediate housing (14), in particular of turbines (11, 13) of a gas turbine engine, having a radially inner bounding wall (23) and having a radially outer bounding wall (24, 24?), having a crossflow channel (33), which is formed by the bounding walls (23, 24, 24?) and within which at least one supporting rib (15) is positioned that has a leading edge (16), a trailing edge (17), as well as side walls (18) extending between the leading edge (16) and the trailing edge (17) that direct a gas flow traversing the crossflow channel (33); the radially outer bounding wall (24) having a contour that changes in the circumferential direction at least in one section upstream of the supporting rib (15).
    Type: Grant
    Filed: January 16, 2012
    Date of Patent: July 5, 2016
    Assignee: MTU Aero Engines GmbH
    Inventors: Martin Hoeger, Inga Mahle, Jochen Gier
  • Patent number: 9188134
    Abstract: A flow machine 10 for a fluid shown contains a radial sealing gap (9) which is formed between stator parts (4, 4a, 4b) and a closed impeller (3) of the flow machine, with at least one wear ring (5) arranged in a stationary manner being provided at the sealing gap and having an inner side facing the impeller, an outer side and two axially spaced apart side surfaces. A concentrically extending recess (6) in the form of a radial gap or of a radial incision is formed in the wear ring (5), with the recess 6, starting from one of the side surfaces, extending in the axial direction over more than a fifth of the axial length of the wear ring and with the wear ring (5) being produced from metal, hard metal or a ceramic material.
    Type: Grant
    Filed: December 14, 2011
    Date of Patent: November 17, 2015
    Assignee: Sulzer Management AG
    Inventor: Martin Üre Villoria
  • Patent number: 9169740
    Abstract: An abrasive coating on a rotor shaft interacts with cantilevered vanes to form an abradable air seal in a turbine engine. The abrasive coating includes a metal bond coat, and an abrasive layer containing a plurality of abrasive CBN grit particles in a ceramic matrix.
    Type: Grant
    Filed: October 25, 2010
    Date of Patent: October 27, 2015
    Assignee: United Technologies Corporation
    Inventors: Christopher W. Strock, Paul H. Zajchowski
  • Patent number: 9157448
    Abstract: Various systems and apparatuses are provided for a turbulence member for an annular seal cavity in a fluid handling device. In one example, the turbulence member includes an inner face positioned to cooperate with a seal assembly in the annular seal cavity to define an inner channel. The turbulence member also includes an outer face positioned to cooperate with a housing to define an outer channel in the annular seal cavity. The turbulence member also includes a front face extending between the inner face and the outer face, and a rear face spaced from the front face and extending between the inner face and the outer face. The turbulence member is configured to disrupt fluid flow within the annular seal cavity and inhibit formation of an air pocket adjacent to the seal assembly.
    Type: Grant
    Filed: April 3, 2012
    Date of Patent: October 13, 2015
    Assignee: General Electric Company
    Inventors: Jeremy William Smith, William Edward Gray
  • Patent number: 9109459
    Abstract: A self-cleaning hydrodynamic face seal for use with a rotary machine is provided. The hydrodynamic face seal includes a seal ring having a radially-extending seal face. In addition, the hydrodynamic face seal includes at least one brush coupled to the seal ring. The at least one brush includes a plurality of flexible elements extending away from the radially-extending seal face of the face seal ring.
    Type: Grant
    Filed: November 11, 2013
    Date of Patent: August 18, 2015
    Assignee: General Electric Company
    Inventors: Shaik Karimulla Sha, Xiaoqing Zheng, Azam Mihir Thatte
  • Patent number: 9057383
    Abstract: A centrifugal compressor is disclosed. The centrifugal compressor comprises a first duct configured to receive a process gas, an impeller connected to the first duct and configured to compress the process gas, wherein the impeller has an outer surface, a first seal comprising, a first plurality of swirl brakes configured to have a tooth shape to reduce the inlet seal swirl of a flow of the process gas at an entrance to the first seal, wherein each swirl brake is disposed at a leading edge of the first seal and is configured to have a gap between the first plurality of swirl brakes and the outer surface of the impeller seal. A seal including a plurality of swirl brakes for reducing an inlet swirl and a method of manufacturing such a seal are disclosed.
    Type: Grant
    Filed: December 20, 2011
    Date of Patent: June 16, 2015
    Assignee: Nuovo Pignone S.P.A
    Inventors: Giuseppe Vannini, Lorenzo Naldi
  • Publication number: 20150125277
    Abstract: A turbocharger bearing system comprising a shaft (211) including at least one shoulder (A2) with a rotor (212) disposed on the shaft (211). First and second bearing sleeves (254) are disposed on the shaft (211) at opposite ends of the rotor (212). Each bearing sleeve (254) includes a collar (213) and a journal portion (225). A journal bearing (249) is disposed on each journal portion (225) and the journal portion (225) of the first bearing sleeve (254) abuts the shoulder (A2) of the shaft (211). In certain aspects of the technology described herein, the bearing sleeves (254) may be oriented in opposite directions. The shaft (211) is the same diameter where the bearing sleeves (254) are positioned. Accordingly, the bearing sleeves (254) may be interchangeable, as well as the journal bearings (249).
    Type: Application
    Filed: April 19, 2013
    Publication date: May 7, 2015
    Inventor: Daniel N. Ward
  • Publication number: 20150125276
    Abstract: A bearing holding structure includes a base and at least one bearing. The base includes a bearing cup, which is axially extended from a center of the base and defines a receiving space therein. The bearing is fitted in the receiving space of the bearing cup and has a shaft hole. At least one groove is provided on one or both of an inner surface of the bearing cup and an outer surface of the bearing; and the groove is communicable with the receiving space of the bearing cup. The groove is filled with a meltable filler, which is melted by laser welding to fixedly connect the bearing and the bearing cup to one another, such that the bearing is not brought by a rotary shaft to rotate and slide in the bearing cup, enabling the bearing and the bearing cup to have prolonged service life.
    Type: Application
    Filed: November 1, 2013
    Publication date: May 7, 2015
    Applicant: Asia Vital Components Co., Ltd.
    Inventors: Kuo-Chen Chang, Kuo-Chieh Chao
  • Publication number: 20150125278
    Abstract: The present invention relates to a seal configuration (100) for a turbo machine having a rotor (5), wherein the seal configuration (100) has a sealing element (300) to create a seal with respect to the rotor (5) in an installed position and a supporting device (200). The supporting device (200) has, in at least one section of the supporting device, a material (9) that melts when it comes into contact with the rotating rotor (5) in the installed position. The present invention further relates to a turbo machine having a seal configuration (100).
    Type: Application
    Filed: November 4, 2014
    Publication date: May 7, 2015
    Inventors: Andre WERNER, Stephan Klaen, Manuel Hertter, Frank Stiehler
  • Patent number: 9011083
    Abstract: A seal arrangement for a gas turbine is disclosed. The seal arrangement is used for sealing a gap between radially internally located ends of guide vanes of a guide vane ring and a rotor, in which case the rotor has at least two seal projections positioned at an axial distance relative to each other in a circumferential direction of the rotor. The seal projections effecting a seal of the gap in combination with intake linings associated with the radially internally located ends of the guide vanes. The seal projections are inclined or tilted in the axial direction toward a side of higher pressure, where, in a space limited by the minimum of two seal projections and the corresponding intake linings, at least one recirculation structure is provided. The recirculation structure, or each recirculation structure, is oriented toward the side of the higher pressure.
    Type: Grant
    Filed: September 30, 2004
    Date of Patent: April 21, 2015
    Assignee: MTU Aero Engines GmbH
    Inventor: Marcello De Martino
  • Publication number: 20150104291
    Abstract: A seal assembly for sealing a fluid passageway from contaminants is disclosed. The fluid passageway is formed by a rotating shaft entering an opening in a housing. The fluid passageway connects an interior of the housing, and any exterior of the housing. The seal assembly includes a first sealing member and a second sealing member, which divides the fluid passage into an interior section, an open section, and a sealed section. The interior section is exposed to the interior of the housing. The sealed section is fluidly sealed between the interior section and the open section. A sensor is disposed within the sealed section. The sensor is configured to sense the contaminants within the sealed section and is electronically coupled to a controller configured to send an alarm signal. The sensor is a moisture sensor and extends into an annular recess formed in the stationary member.
    Type: Application
    Filed: October 9, 2014
    Publication date: April 16, 2015
    Inventors: Randy J. Kosmicki, Michael L. Viken
  • Publication number: 20150098805
    Abstract: A seal assembly of an air cycle machine includes a seal plate with an outer diameter. A bore extends axially through a center of the seal plate and a seal land is disposed at least partially within the bore. The seal land includes an inner diameter and a minimum ratio between the inner diameter of the seal land and the outer diameter of the seal plate is approximately 0.1985.
    Type: Application
    Filed: October 9, 2013
    Publication date: April 9, 2015
    Applicant: Hamilton Sundstrand Corporation
    Inventors: Craig M. Beers, Christopher McAuliffe
  • Publication number: 20150098844
    Abstract: A fan module used in an electronic apparatus is provided. The electronic apparatus includes an upper cover and a lower cover. The fan module includes a fan housing, a fixing shaft, a bearing, and a fan body. The fan housing is mounted on the lower cover. The fixing shaft includes a first end and a second end. The first end is mounted on the fan housing. The second end passes out of the fan housing. The bearing includes a first ring and a second ring. The first ring is pivotally connected to the second ring. The first ring is disposed around the outer edge of the fixing shaft. The fan body is disposed around the outer edge of the second ring, so as to rotate relative to the fixing shaft.
    Type: Application
    Filed: May 11, 2014
    Publication date: April 9, 2015
    Inventors: I-Feng HSU, Chang-Yuan WU, Chih-Chin CHIEN
  • Patent number: 8998569
    Abstract: A gas turbine engine includes a gas turbine engine internal compartment structure having an integral passageway. Wiring is routed through the integral passageway of the gas turbine engine internal compartment structure.
    Type: Grant
    Filed: August 17, 2011
    Date of Patent: April 7, 2015
    Assignee: United Technologies Corporation
    Inventor: Russell B. Witlicki
  • Patent number: 8991176
    Abstract: A turbocharger for an internal combustion engine includes a shaft, a first turbine wheel, a compressor wheel, and a second turbine wheel. The shaft includes a first end and a second end and is supported for rotation about an axis. The first turbine wheel is mounted on the shaft proximate to the first end and configured to be rotated about the axis by post-combustion gasses emitted by the engine. The compressor wheel is mounted on the shaft between the first and second ends and configured to pressurize an airflow being received from the ambient for delivery to the engine. The second turbine wheel is mounted on the shaft proximate to the second end and configured to be rotated about the axis by a pressurized fluid. An internal combustion engine employing such a turbocharger is also disclosed.
    Type: Grant
    Filed: March 28, 2012
    Date of Patent: March 31, 2015
    Assignee: GM Global Technology Operations LLC
    Inventors: Louis P. Begin, Carnell E. Williams
  • Publication number: 20150050130
    Abstract: A sealing device between two axisymmetric coaxial parts, includes an elastic segment, two holding elements located on each side of the annular segment, an annular spacer arranged between the two holding elements, wherein the annular spacer has a notch around its peripheral rim; the annular elastic segment has a hooking element at each of its free ends, adapted to cooperate with the notch of the annular spacer, and to hold the elastic segment in a pre-holding position by elastic return force.
    Type: Application
    Filed: January 7, 2013
    Publication date: February 19, 2015
    Inventors: Serge René Morreale, Arnaud Jean-Marie Pierrot
  • Publication number: 20150023780
    Abstract: A gas turbine engine includes a liner disposed around a flowpath. The liner has a forward end, a radially outer surface, and a radially inner surface. A hole extends axially into the forward end of the liner between the radially outer surface and the radially inner surface, and an engagement member is partially disposed in the hole and extends axially forward from the forward end of the liner.
    Type: Application
    Filed: July 2, 2014
    Publication date: January 22, 2015
    Inventors: Mark W. Costa, Thomas J. Robertson, JR., David A. Welch
  • Publication number: 20150010392
    Abstract: A water pump apparatus is provided having a plurality of modular components, which allows for construction of various configurations of the water pump apparatus depending on specific vehicle requirements. The water pump apparatus modular components include a pump housing with a fluid chamber formed therein, a bearing housing for attachment to the pump housing, and a thermostat housing for connecting to the bearing housing and the pump housing. A method for forming modular components for assembling a water pump apparatus for use in an internal combustion engine is also provided.
    Type: Application
    Filed: January 18, 2012
    Publication date: January 8, 2015
    Applicant: International Engine Intellectual Property Company LLC
    Inventors: Ivan M. Lazich, Bienvenido L. Yadao, JR.
  • Publication number: 20150003957
    Abstract: A turbine assembly for a turbocharger can include a C-shaped seal that includes an inner diameter, an outer diameter, an axis aligned parallel to a rotational axis of a turbine wheel, a lower lip that contacts a lower axial face of an outer surface of a shroud component along an annular portion of the shroud component, an upper lip that contacts a lower axial face of an inner surface of a turbine housing, and a wall portion that extends between the lower lip and the upper lip. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.
    Type: Application
    Filed: June 26, 2013
    Publication date: January 1, 2015
    Inventors: Arnaud Gerard, Shankar Pandurangasa Solanki, Nicolas Morand, Sylvain Mulot, Vincent Eumont, Francis Abel, Stephane Sibille
  • Publication number: 20140377057
    Abstract: A sealing device in which coming off from the housing is suppressed with a simple structure even when the housing is made of resin. A case 110 is characterized in that it has a cylindrical portion 111 to be fitted into the inner circumferential surface of a small diameter portion 31, a flange portion 112 extending to the outer circumferential side from an end of the cylindrical portion 111 and abutting against a step surface 32 between the small diameter portion 31 and a large diameter portion 33 so that the sealing device 100 is positioned, and a tab portion 113 configured such that it inclines to the outer circumferential side as it extends from the end of the flange portion 112 in the axial direction away from the cylindrical portion 111.
    Type: Application
    Filed: April 1, 2013
    Publication date: December 25, 2014
    Applicant: EAGLE INDUSTRY CO., LTD.,
    Inventor: Koichiro Oiyama
  • Publication number: 20140369820
    Abstract: An exhaust-gas turbocharger (1) comprising a compressor (2); a turbine (3); and a bearing housing (4), in which there is arranged a bearing cartridge (5), secured against axial displacement and twisting; and a single fixing element (6) securing the bearing cartridge (5) both against axial displacement and also twisting in the bearing housing (4). Also a method for assembling a bearing cartridge (5) in a bearing housing (4) of an exhaust-gas turbocharger (1).
    Type: Application
    Filed: January 22, 2013
    Publication date: December 18, 2014
    Applicant: BorgWarner Inc.
    Inventor: Silvio Koch
  • Publication number: 20140369819
    Abstract: In a method for manufacturing an anti-rotation ring of a scroll type compressor, wherein the anti-rotation ring is provided in an anti-rotation mechanism for preventing a movable scroll from rotation on its own axis and made of a metal, the steps of the method include drawing a steel plate into a first intermediate body having a bottomed cylindrical shape, punching the bottom of the first intermediate body thereby to make a second intermediate body and ring forming the second intermediate body.
    Type: Application
    Filed: June 6, 2014
    Publication date: December 18, 2014
    Inventors: Takuro YAMASHITA, Ken SUITOU, Hiroyuki GENNAMI
  • Publication number: 20140356141
    Abstract: A gas turbine engine includes a bearing. A bearing support includes a first wall that extends between the first and second ends and is operatively supported by the bearing at a first end. An engine case is secured to the second end radially outward of the first end. A flexible support is provided by a second wall integral with and extending transversely from the first wall. The second wall has a first flange and a gear train component is secured to the first flange.
    Type: Application
    Filed: August 15, 2014
    Publication date: December 4, 2014
    Inventor: Todd A. Davis
  • Publication number: 20140356145
    Abstract: Embodiments of the present disclosure are directed towards a seal assembly including a first seal and a second seal, wherein the first seal and the second seal axially abut one another within a retaining bore of a compressor, and cooperatively form an outer radial contour of the seal assembly that is retained by the retaining bore.
    Type: Application
    Filed: May 30, 2013
    Publication date: December 4, 2014
    Inventors: Thomas Edward Gerber, Jonathan David Clemons
  • Publication number: 20140356140
    Abstract: Embodiments of the present disclosure are directed towards an annular bearing retainer ring comprising a first axial surface, wherein the first axial surface is planar, and a second axial surface, wherein the second axial surface is non-planar.
    Type: Application
    Filed: May 30, 2013
    Publication date: December 4, 2014
    Inventors: Noel D. Blair, JR., Thomas Edward Gerber
  • Publication number: 20140348643
    Abstract: To impede soot leakage around a shaft which extends through a bore connecting volumes of differing pressures, e.g., a turbocharger turbine housing and the ambient air, a soot seal is provided to capture particulate matter while allowing the passage of gas.
    Type: Application
    Filed: September 6, 2012
    Publication date: November 27, 2014
    Applicant: BORGWARNER INC.
    Inventor: Timothy House
  • Publication number: 20140348642
    Abstract: A device including a conjoined laminate interface seal shaped for reducing inter-seal gap (e.g., an angled gap, an ‘L’-shaped gap, etc.) leakage in gas turbines is disclosed. In one embodiment, a seal device for a gas turbine includes: a first flange shaped to be disposed within a first slot of a first arcuate component and a first adjacent slot of a second arcuate component; a conjoined layer connected to a first surface of the first flange, the first surface configured to face a working fluid flow of the gas turbine; and a second flange shaped to be disposed within a second slot of the first arcuate component and a second adjacent slot of the second arcuate component, the second flange including a second surface connected to the conjoined layer.
    Type: Application
    Filed: May 2, 2013
    Publication date: November 27, 2014
    Applicant: General Electric Company
    Inventor: General Electric Company
  • Publication number: 20140341720
    Abstract: Systems and devices configured to seal interfaces/gaps between stationary components of turbines and manipulate a flow of coolant about portions of the turbine during turbine operation are disclosed. In one embodiment, a seal element includes: a first surface shaped to be oriented toward a pressurized cavity of the turbine; a second surface oriented substantially opposite the first surface and shaped to sealingly engage a contact surface of the static components; and a first set of angular features disposed in the second surface, the first set of angular features fluidly connecting the pressurized cavity and the flowpath of the turbine.
    Type: Application
    Filed: May 14, 2013
    Publication date: November 20, 2014
    Inventors: Dipankar Pal, Robert Walter Coign, Gary Michael Itzel, Kevin Thomas McGovern, Christopher Donald Porter
  • Publication number: 20140334919
    Abstract: In a foundation in which both ends of a turbine rotor are arranged in the foundation and are freely rotatably supported by bearings, there are provided rectangular notches extending over a prescribed vertical depth from the top face of a wall surface on the casing side of a concrete section, having prescribed width and horizontal depth; bearing support members formed with an extension are laid in these notches; the bearings are installed on these extensions.
    Type: Application
    Filed: July 22, 2014
    Publication date: November 13, 2014
    Applicant: Kabushiki Kaisha Toshiba
    Inventor: Masato MISAWA