With Lubricating, Sealing, Packing Or Bearing Means Having Internal Working Fluid Connection (e.g., Fluid Or Fluid Biased Seal, Etc.) Patents (Class 415/110)
  • Patent number: 11022130
    Abstract: This turbocharger (1A) is provided with: a rotating shaft (4); a turbine wheel (2); a compressor wheel (3); a bearing housing (6) provided with journal bearings (5A, 5B) for rotatably supporting a shaft (4), and a thrust bearing (8) for supporting the rotating shaft (4) in the center axis (C) direction thereof; and a turbine housing (31) in which the turbine wheel (2) is accommodated. A fluid supply section (70A) for supplying a fluid to the turbine wheel (2) is provided within the turbine housing (31) and said fluid presses the turbine wheel (2) toward a first end (4a) side.
    Type: Grant
    Filed: March 30, 2016
    Date of Patent: June 1, 2021
    Assignee: MITSUBISHI HEAVY INDUSTRIES ENGINE & TURBOCHARGER, LTD.
    Inventors: Yutaka Fujita, Takao Yokoyama, Seiichi Ibaraki
  • Patent number: 11015592
    Abstract: An apparatus and associated method for operating a horizontal surface pump apparatus, including a motor operating a pump to pressurize a fluid inside the pump. A flow controller executes computer instructions stored in memory that define a selected flow rate of the fluid flowing out of the pump based on a flow profile trajectory stored in memory and related to an observed parameter of the fluid. A motor controller executes computer instructions stored in memory that map the selected flow rate and an observed head pressure of the fluid to a selected motor speed via a transformation function stored in memory, and that operate the motor at the selected motor speed.
    Type: Grant
    Filed: November 26, 2018
    Date of Patent: May 25, 2021
    Assignee: Villicus, Inc.
    Inventors: Russell Self, Bill Mann
  • Patent number: 10968774
    Abstract: There is disclosed an assembly for a gas turbine engine that includes a bearing housing circumferentially extending around a central axis thereof and delimiting a bearing cavity for receiving a bearing therein. A controlled gap seal is secured to the bearing housing, the controlled gap seal including a ring and a runner, the runner rotatable relative to the ring about the central axis, the runner spaced apart from the ring by a gap. The gap defines a fluid passage between the bearing cavity and an environment outside the bearing cavity. At least one baffle is secured to a surface of the bearing housing oriented toward the bearing cavity. The at least one baffle is a fin protruding from the surface and extending into the bearing cavity. The at least one baffle disrupts a cylindricality of the surface. A method of operating the bearing assembly is also disclosed.
    Type: Grant
    Filed: November 20, 2018
    Date of Patent: April 6, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Ignatius Theratil, Aldo Abate, Nicola Houle
  • Patent number: 10934867
    Abstract: A stationary-blade-type rotating machine is provided with a rotational shaft, an impeller, an impeller housing having a scroll passage formed on an outer peripheral side of the impeller, a bearing housing connected to the impeller housing in an axial direction of the rotational shaft, a stationary blade disposed in a radial passage formed between the scroll passage and the impeller and defined by an impeller-housing-side member and a bearing-housing-side member which face each other in the axial direction of the rotational shaft. The fixation unit includes an annular circumferential groove formed in an inner peripheral surface of the impeller housing and a ring-shaped fitting member subjected to a force for expanding in a radial direction while being fitted into the circumferential groove. The fitting member is configured to press the stationary blade to the impeller housing via at least one of the impeller-housing-side member or the bearing-housing-side member.
    Type: Grant
    Filed: January 20, 2016
    Date of Patent: March 2, 2021
    Assignee: MITSUBISHI HEAVY INDUSTRIES ENGINE & TURBOCHARGER, LTD.
    Inventors: Kazuya Takeda, Takashi Shiraishi, Kazuki Okuda, Takeshi Yoshimi, Toshimasa Igusa
  • Patent number: 10907608
    Abstract: The present invention generally relates to hydraulic machinery, such as hydraulic turbines. More specifically, the invention is directed to optimizing power consumption when the turbine is used in condenser mode. The present invention provides a novel hydraulic installation where the reduction of pressure in the spiral case during condenser mode operations is more efficient, limiting the power consumption if compared to state-of-the-art installations.
    Type: Grant
    Filed: September 9, 2016
    Date of Patent: February 2, 2021
    Inventors: Renaud Guillaume, Pierre Yves Lowys, Arnaud Legrand, Philippe Girin
  • Patent number: 10883518
    Abstract: A water pump cooler for CPU wherein coolant may efficiently perform heat exchange, comprising at least: at least a heat absorbing component, at least a heat-transfer water pump, at least a heat exchange component and connecting water pipes, wherein a closed loop is formed by the heat-transfer water pump, connecting water pipes and heat exchange component. The heat-transfer water pump is disposed above the heat absorbing component to serve as a cycle power source for the coolant. The heat-transfer water pump includes at least a water pump component, which includes at least a base plate and a plurality of rotor axial impeller sections and rotor centrifugal impeller sections. The coolant is driven by the rotor axial impeller sections to flow into the rotor centrifugal impeller sections, and is then thrown at a high speed by the rotor centrifugal impeller sections to the heat exchange component for efficient heat dissipation.
    Type: Grant
    Filed: June 28, 2017
    Date of Patent: January 5, 2021
    Assignee: Dongguan Zhenpin Hardware Cooling Technology Co. Ltd
    Inventors: Bao Hua Sheng, Hong Yan Liao
  • Patent number: 10815805
    Abstract: A turbine interstage structure for a gas turbine engine that includes a first stage disk and a second stage disk. A central plenum is defined by a an inner band for supporting nozzle vanes, a forward stator plate and an aft stator plate wherein the forward stator plate is spaced-apart from the aft stator plate, and an inner boundary. A forward mid-seal positioned between the inner boundary and the forward stator plate. An aft mid-seal positioned between the inner boundary and the aft stator plate; and wherein the inner boundary is a solid annular component.
    Type: Grant
    Filed: January 20, 2017
    Date of Patent: October 27, 2020
    Assignee: General Electric Company
    Inventors: Steven Douglas Johnson, Nicholas R. Dinsmore, Daniel Tyler Jarboe
  • Patent number: 10801365
    Abstract: A turbine engine that includes an engine casing including a fluid supply plenum, a mating surface, and a nozzle supply passage and a cavity flow passage that both extend between the fluid supply plenum and the mating surface. The turbine engine further includes a turbine nozzle assembly including a mating band. The mating band includes an inlet scoop in flow communication with the nozzle supply passage. An interface is defined between the mating band and a first portion of the mating surface, and a band cavity is defined between the mating band and a second portion of the mating surface. The cavity flow passage couples the fluid supply plenum in flow communication with the band cavity.
    Type: Grant
    Filed: February 27, 2018
    Date of Patent: October 13, 2020
    Assignee: General Electric Company Polska sp. z o.o.
    Inventors: Leszek Marek Rzeszutek, Dariusz Olczak, Grzegorz Maciej Kaczmarek, Tomasz Bulsiewicz, Maciej Michal Stanczyk, Adam Tralewski
  • Patent number: 10763524
    Abstract: A fuel cell module comprises a hydrogen pump including a pump side facing surface having a pump side opening, a gas-liquid separator including a separator side facing surface having a separator side opening, three or more fastening points at which the hydrogen pump and the gas-liquid separator are fastened to each other, a heating flow path, a gasket that seals a connection portion, at which the pump side opening and the separator side opening are connected to each other, and an inclination preventing portion formed by an elastic member. At least a part of the gasket is disposed outside an area defined by lines connecting the three or more fastening points to each other, and between the pump side facing surface and the separator side facing surface, and the inclination preventing portion is disposed within the area, and between the pump side facing surface and the separator side facing surface.
    Type: Grant
    Filed: June 7, 2018
    Date of Patent: September 1, 2020
    Assignee: TOYOTA JIDOSHA KABUSHIKI KAISHA
    Inventor: Tomoyuki Kozuka
  • Patent number: 10753214
    Abstract: A gas turbine unit having a combustor having a liner, a turbine, arranged downstream of the liner along a main flow gas direction and including a plurality of first stage vanes, a rotor cover support located inwardly of the vanes, and a sealing arrangement at a combustor to turbine interface, wherein the sealing arrangement includes a first dogbone seal extending between the rotor cover support and an inner downstream end of the liner or between the rotor cover support and a bulkhead located at the inner downstream end of the liner.
    Type: Grant
    Filed: July 14, 2017
    Date of Patent: August 25, 2020
    Assignee: ANSALDO ENERGIA SWITZERLAND AG
    Inventors: Jost Imfeld, Hans-Christian Mathews, Urs Benz
  • Patent number: 10711621
    Abstract: A turbine vane assembly adapted for use in a gas turbine engine includes a support and a turbine vane arranged around the support. The support is made of metallic materials. The turbine vane is made of ceramic matrix composite materials to insulate the metallic materials of the support.
    Type: Grant
    Filed: February 1, 2019
    Date of Patent: July 14, 2020
    Assignee: Rolls-Royce plc
    Inventor: Michael J. Whittle
  • Patent number: 10571126
    Abstract: Manufactured articles, and methods of manufacturing enhanced wear protected components and articles. More particularly, wear protected components and articles, such as combustor components of turbine engines, and even more particularly enhanced wear protected micromixer tubes and assemblies thereof with one or more micromixer plates, the micromixer tubes having wear protection for enhanced performance and reduced wear related failure. Methods including surface treatment to enhance wear, including vacuum braze application of coatings to enhance surface hardness for wear benefits.
    Type: Grant
    Filed: February 8, 2017
    Date of Patent: February 25, 2020
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Dechao Lin, Srikanth Chandrudu Kottilingam, Brian Lee Tollison, Yan Cui
  • Patent number: 10544702
    Abstract: A gas turbine engine that includes a turbine interstage region. The turbine interstage region is configured to conduct bore bleed air outwardly. The interstage region includes a central plenum. The interstage region also includes a first mid-seal and a second mid-seal. The central plenum is fluidly connected to bore bleed air by a flow circuit that passes between the first mid-seal and the second mid-seal.
    Type: Grant
    Filed: January 20, 2017
    Date of Patent: January 28, 2020
    Assignee: General Electric Company
    Inventors: Steven Douglas Johnson, Nicholas R. Dinsmore, Daniel Tyler Jarboe
  • Patent number: 10544699
    Abstract: A component and method for minimizing a gap between a blade platform ledge and a vane platform ledge in a turbine engine. The blade platform supports turbine blades attached to a shaft. The movable blade platform is positioned adjacent to a stationary vane platform having vanes mounted on an outer surface. The blade and vane platforms are separated by the gap between the platform ledges. During manufacture, an abrasive coating is applied to the surface of the blade platform ledges so that the coating contacts the vane platform ledge when the engine is started. The abrasive coating on the turbine blade platform cuts the surface of the vane platform ledge to form a gap sufficient to permit unobstructed motion of the blade platform, yet of minimal size to limit the flow of gas between the space within and the space outside the platforms.
    Type: Grant
    Filed: December 19, 2017
    Date of Patent: January 28, 2020
    Assignee: ROLLS-ROYCE CORPORATION
    Inventor: Neil Anthony Clayton
  • Patent number: 10465601
    Abstract: A variable nozzle unit in a variable-capacity supercharger includes: a first nozzle ring disposed in a turbine housing and formed with a plurality of first support holes; a second nozzle ring disposed to face the first nozzle ring and formed with a plurality of second support holes that are through-holes corresponding to the first support holes; a plurality of variable nozzles supported rotatably by the first and second nozzle rings; and a plurality of seal members disposed between a turbine scroll channel and a turbine wheel side. The variable nozzles include first nozzle shafts that are rotatably supported by the first support holes, and second nozzle shafts that are rotatably supported by the second support holes, and a first seal member included in the plurality of seal members is provided at the turbine wheel side relative to the second support holes.
    Type: Grant
    Filed: September 17, 2015
    Date of Patent: November 5, 2019
    Assignee: IHI Corporation
    Inventors: Kengo Ikeda, Yoshimitsu Matsuyama
  • Patent number: 10458272
    Abstract: The present application concerns a test engine hood for a turbine engine, such as a double flow turbine. The test hood allows replacement of a flight engine hood during tests on a test bench on the ground where the temperature conditions could damage the flight hood. The test hood includes a tubular wall of carbon-fiber epoxy composite, and metal flanges upstream and downstream. To provide thermal protection, the test hood includes a layer of silicone with a majority of polysiloxane. The layer covers the entire inner surface of the wall to create a barrier. The present application also concerns a method for testing a turbine engine on a test bench, where the turbine engine is fitted with a test casing. The present application also concerns a use of silicone for thermal insulation of the inside of the test hood of the turbine engine on a test bench on the ground.
    Type: Grant
    Filed: September 28, 2015
    Date of Patent: October 29, 2019
    Assignee: SAFRAN AERO BOOSTERS SA
    Inventors: Quac Hung Tran, Pierre Croes, Aurore Noelmans
  • Patent number: 10364748
    Abstract: A seal includes two layers, each layer including a base and fingers extending from the base. The fingers are separated by slots and the fingers include orifices. The slots of each layer are laterally spaced apart from each other. The orifices of one of the layers are partially overlapped by the orifices of the other layer so that the areas of the partially overlapped orifices extend beyond the areas of the overlapping orifices.
    Type: Grant
    Filed: August 19, 2016
    Date of Patent: July 30, 2019
    Assignee: United Technologies Corporation
    Inventor: John D Teixeira
  • Patent number: 10344616
    Abstract: A stator device for a continuous-flow machine with guide vanes circumferentially distributed on a housing. The guide vanes are respectively embodied with a blade leaf and at least one platform. The platforms form a surface of an annular channel through which working fluid flows. A flow area is provided via which, during operation of the stator device, a working fluid flows on a side of the platform that is facing away from the annular channel from a pressure side of the blade leaf to a suction side of the blade leaf at least in certain areas in the radial direction of the stator device. At least one suction appliance is provided which adjoins the flow area and is formed by a recess, and via which working fluid can be conducted out of the flow area during operation of the stator device.
    Type: Grant
    Filed: June 24, 2016
    Date of Patent: July 9, 2019
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Patrick Grothe
  • Patent number: 10329929
    Abstract: A disc of a gas turbine engine system with particular retaining ring placement and engagement implementation are provided. For example, the disc includes a disc bore including, a groove formed on an axially extending surface of the disc bore, wherein the groove includes a forward surface that extends radially into the disc bore to a groove floor that is cut into the disc bore and extends axially to an aft surface that extends radially outward to at least the axially extending surface of the disc bore, and a scallop formed along at least one surface of the groove, wherein the scallop is configured to provide a flow path, and a disc web that extends radially outward from the disc bore, relative to an axis of rotation of the gas turbine engine.
    Type: Grant
    Filed: March 15, 2016
    Date of Patent: June 25, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Nicholas Waters Oren, Steven D. Porter
  • Patent number: 10233842
    Abstract: A tangential on-board injector (TOBI) for a gas turbine engine and methods of making the same are provided. The TOBI includes at least one adjustable strut configured to control an airflow through the TOBI, the at least one adjustable strut moveable to change an airflow characteristic within the TOBI.
    Type: Grant
    Filed: January 8, 2016
    Date of Patent: March 19, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Carey Clum, Thomas N. Slavens
  • Patent number: 10208614
    Abstract: Apparatuses are disclosed including a first article, a second article, a sewing member and a thermal break. The second article includes a second material composition having a second thermal tolerance greater than a first thermal tolerance of a first material composition of the first article. The sealing member is disposed between and contacts the first article and the second article, and includes a third material composition having a third thermal tolerance less than the second thermal tolerance and less than an operating temperature of the second article. The thermal break is defined by the second article, and is proximate to the sealing member and partitioned from the sealing member by a portion of the second article. The thermal break interrupts a thermal conduction path from the second article to the sealing member. The first article and the second article compress the sealing member, forming a thermal gradient-tolerant seal.
    Type: Grant
    Filed: February 26, 2016
    Date of Patent: February 19, 2019
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Matthew Troy Hafner, Gary Michael Itzel, Sandip Dutta
  • Patent number: 10203281
    Abstract: A transmitted light intensity measurement unit for measuring a concentration of fluid flowing through a duct comprises: a light source for supplying light into the duct from a light supply part on a surface of the duct; a light receiving element for receiving the light, which has been passed from the light supply part through the duct wall and the fluid inside the duct, at a light receiving part located on an opposite side in a diametrical direction of the duct relative to the light supply part, and outputs a signal indicating an intensity of the light; and a light-transmissive member disposed on at least one light path among a light pass between the light source and the light supply part and a light pass between the light receiving element and the light receiving part, abutting and closely contacting the duct wall by an elastic deformation of the duct wall.
    Type: Grant
    Filed: May 27, 2016
    Date of Patent: February 12, 2019
    Assignees: NIPRO CORPORATION, HARADA ELECTRONICS INDUSTRY CO., LTD.
    Inventors: Yoshihiko Sano, Masahide Harada
  • Patent number: 10167723
    Abstract: A gas turbine engine includes a turbine section fluidly connected to a combustor by a primary flow path. The turbine section includes a first portion at a high pressure relative to a second portion. A thermally isolated cooling plenum is positioned radially inward of the primary flow path. The cooling plenum is defined by a forward wall, a shaft structure, an aft wall, and an inner diameter wall of the primary flow path. Air in the thermally isolated cooling plenum is thermally isolated from air in the primary flow path. At least one cooling air system is operable to provide cooling air to the thermally isolated cooling plenum.
    Type: Grant
    Filed: June 3, 2015
    Date of Patent: January 1, 2019
    Assignee: United Technologies Corporation
    Inventors: Gabriel L Suciu, Brian D Merry, James D Hill
  • Patent number: 10161257
    Abstract: A gas turbine engine arcuate leaf seal assembly includes arcuate leaf seal extending radially and circumferentially between adjacent first and second turbine components. Upper and lower leaf seal portions of leaf seal are in radially spaced apart arcuate upper and lower grooves in the first and second turbine components respectively. The seal includes an arcuate body and a circumferential retention tab extending radially away from body and disposed in a notch in a wall of grooves. Seal may have a thickness between 3 mils and 35 mils and/or torsional stiffness between 0.015 and 0.15 lb/in. Turbine components may be radially adjacent turbine nozzle upper and lower components. The upper or lower component may be made of a ceramic matrix composite material. Annular cooling air plenum including flow cavities in inner support ring segments may be in lower component and in flow communication with hollow fairing airfoils.
    Type: Grant
    Filed: October 20, 2015
    Date of Patent: December 25, 2018
    Assignee: General Electric Company
    Inventors: Benjamin Scott Huizenga, Kevin Robert Feldmann, Robert Alan Frederick, Robert Charles Groves, II, Kirk Douglas Gallier, Timothy Francis Andrews, Darrell Senile
  • Patent number: 10161305
    Abstract: A circular ring-shaped shroud plate is arranged between a scroll passage and a turbine chamber. The shroud plate has a through-hole that penetrates therethrough in a direction along an axis of a turbine shaft. A variable nozzle is supported in an openable/closable manner on the shroud plate by a shaft inserted through the through-hole. A gap between the shroud plate and a turbine housing in the direction along the axis is partitioned into a first space that communicates with an outlet of exhaust gas that faces the through-hole and is provided upstream of a turbine wheel with respect to the flow of exhaust gas, and a second space that communicates with the scroll passage, by a disc spring that is so arranged as to surround the turbine wheel.
    Type: Grant
    Filed: November 13, 2012
    Date of Patent: December 25, 2018
    Assignees: Toyota Jidosha Kabushiki Kaisha, Kabushiki Kaisha Toyota Jidoshokki
    Inventors: Hiroaki Ikegami, Tsuyoshi Uesugi
  • Patent number: 10132191
    Abstract: A variable area turbine arrangement according to an exemplary aspect of the present disclosure includes, among other things, a variable vane assembly and a secondary flow system associated with the variable vane assembly. Flow modulation of a cooling fluid through the secondary flow system is changed simultaneously with actuation of the variable vane assembly.
    Type: Grant
    Filed: August 13, 2014
    Date of Patent: November 20, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Raymond Surace, Eric A. Hudson
  • Patent number: 10072507
    Abstract: An airfoil attachment according to one example of this disclosure includes an airfoil and a disk supporting the airfoil. Further, there are primary contact surfaces and secondary contact surfaces between the airfoil and the disk. The secondary contact surfaces are not engaged during a normal operating condition.
    Type: Grant
    Filed: October 25, 2012
    Date of Patent: September 11, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: David P. Houston
  • Patent number: 10072576
    Abstract: A gas turbine cooling system efficiently cools a first-stage turbine wheel and attachment portions of first-stage turbine blades. The gas turbine cooling system includes a group of impingement cooling holes provided in a partition wall as a stationary component that separates an exit space of a compressor and a wheel space located upstream of a turbine wheel for ejecting compressed air in the exit space toward the turbine wheel and attachment portions of the turbine blades.
    Type: Grant
    Filed: November 18, 2014
    Date of Patent: September 11, 2018
    Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.
    Inventors: Tomoyuki Matsui, Hayato Maekawa, Ryo Kawai
  • Patent number: 10041500
    Abstract: A gas turbine engine endwall treatment includes a recirculation passages distributed circumferentially around and extending generally axially in an endwall or shroud, Venturi effect producing main throats between main inlet and outlet passages including main inlet and outlet ports respectively extending through the endwall or shroud, and main inlet ports axially aft and downstream of the main outlet ports. Second inlet passages may connect second inlet ports in endwall to main recirculation passages at or near main throats and second inlet ports. An annular groove in endwall may pass through and interconnect the second inlet ports. Two or more clustered inlet passages may extend from two or more clustered secondary inlet ports to two or more intersections of the two or more clustered inlet passages and the main recirculation passage. The main inlet and outlet ports may be spaced one or more stages apart.
    Type: Grant
    Filed: December 8, 2015
    Date of Patent: August 7, 2018
    Assignee: General Electric Company
    Inventor: Josef Anton Streit
  • Patent number: 9988923
    Abstract: One exemplary embodiment of this disclosure relates to a gas turbine engine including a first engine component and a second engine component. The first engine component has a mate face adjacent a mate face of the second engine component. The engine further includes a seal between the mate face of the first engine component and the mate face of the second engine component. The seal establishes three points of contact with each mate face in at least one condition.
    Type: Grant
    Filed: August 29, 2014
    Date of Patent: June 5, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Brooks E. Snyder, Thomas N. Slavens, Mosheshe Camara-Khary Blake
  • Patent number: 9975789
    Abstract: A system includes a fluid injection system. The fluid injection system includes a rotary isobaric pressure exchanger (IPX) configured to receive a first fluid, to receive a second fluid extracted from a source well, to utilize the second fluid to pressurize the first fluid for injection into an injection well, and to inject the pressurized first fluid into the injection well.
    Type: Grant
    Filed: April 13, 2016
    Date of Patent: May 22, 2018
    Assignee: ENERGY RECOVERY, INC.
    Inventors: Farshad Ghasripoor, Jeremy Grant Martin, David Deloyd Anderson, Joel Gay
  • Patent number: 9951786
    Abstract: A centrifugal pump impellor includes balancing holes that reduce axial thrust while minimizing the loss of pump efficiency. In one general aspect, the balancing holes penetrate the rear shroud between the blades, and are angled in both axial and rotational directions so as to direct the leakage fluid approximately parallel to the primary process fluid, so that it causes minimal interference with the primary fluid flow. In a second general aspect, the balancing holes extend from the rear cavity within the impellor blades and through the leading edges of the blades, thereby entering the primary flow in locations where the process fluid is almost static relative to the blades. This minimizes the impact on the flow of the process fluid past the blades, and thereby minimizes the loss of pump efficiency caused by the balance holes. In embodiments, each blade leading edge includes a plurality of balancing hole outlets.
    Type: Grant
    Filed: November 18, 2016
    Date of Patent: April 24, 2018
    Assignee: Flowserve Management Company
    Inventors: Kariem Elebiary, Scott Judge, Edouard Morlac, Mark O'Sullivan
  • Patent number: 9803550
    Abstract: A gas turbine engine comprises a shaft assembly including a hollow shaft of the gas turbine engine and a plug connected to the inlet end of the shaft. The hollow shaft has a shaft bore having a bore diameter. The hollow shaft has an inlet end for receiving a first portion of an incoming air flow. The plug has a plug bore therethrough, and an inlet end having an inlet diameter. The inlet diameter of the plug is smaller than the bore diameter. The plug includes a deflection surface adapted to deflect a second portion of the incoming air flow away from the shaft bore. A plug for connecting to an end of a hollow shaft of a gas turbine engine and s method of controlling a flow of fluid through a shaft having a bore therethrough of a gas turbine engine are also presented.
    Type: Grant
    Filed: March 31, 2014
    Date of Patent: October 31, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Vincent Paradis, Rémy Synnott
  • Patent number: 9683455
    Abstract: A component for releasing a flow of material into an environment subject to periodic fluctuations in pressure, which has: a first surface that includes an inlet; a second surface that includes an outlet; a duct formed in the component and extending from the inlet to the outlet so, when the component is in use, a flow of material received at the inlet can flow along the duct to be released at the outlet into an environment subject to periodic fluctuations in pressure. The duct includes a constriction at which it decreases in cross-sectional area as it progresses from the inlet to the outlet. This can help reduce the variation in flow rate of material released at the outlet caused by the periodic fluctuations in pressure, and may help to avoid/reduce ingestion, when the component is in use. Preferably, the component is configured to form part of a gas turbine engine.
    Type: Grant
    Filed: June 19, 2014
    Date of Patent: June 20, 2017
    Assignee: ROLLS-ROYCE PLC
    Inventors: Thomas Povey, Matthew Christopher John Collins
  • Patent number: 9657641
    Abstract: In a fluid flow machine, especially a gas turbine, axially penetrated by a hot gas stream, the rotor shaft is surrounded by heat shield segments or by base plates of the rotor blades on the rotor side. In the heat shield segments and in the base plates, cooling air chambers are provided, communicating with each other and with a cooling air source, which chambers communicate at least partially with gaps which extend in the longitudinal direction or peripheral direction of the rotor shaft between adjacent rotor blades or between heat shield segments and adjacent base plates of the rotor blades. These gaps are closed off by sealing bands such that a cooling air entry into the hot gas stream is only possible at the ends of the base plates of the rotor blades pointing contrary to the flow direction.
    Type: Grant
    Filed: June 7, 2013
    Date of Patent: May 23, 2017
    Assignee: General Electric Company
    Inventor: Alexander Anatolievich Khanin
  • Patent number: 9506469
    Abstract: An air compressor includes a compressor body, an electric motor, a gear mechanism, a gear casing, a partitioning wall, and a screw seal. The screw seal locates in a through hole formed to the partitioning wall, where a rotating shaft of the electric motor passes through, and makes an air flow from the electric motor side to the gear mechanism side in the through hole with rotating of the rotation shaft. The air compressor also includes a bearing that supports that rotating shaft is arranged to the gear mechanism side of the partitioning wall, such that a rotor of the electric motor has overhang structure. The air compressor also includes a communication hole that communicates the electric motor side from the screw seal of the through hole and an outside of the air compressor not through the internal space of the casing of the electric motor.
    Type: Grant
    Filed: January 30, 2012
    Date of Patent: November 29, 2016
    Assignee: Hitachi Industrial Equipment Systems Co., Ltd.
    Inventors: Kenji Morita, Hideharu Tanaka
  • Patent number: 9441540
    Abstract: According to one embodiment, there is disclosed an inducer assembly for use with a gas turbine engine. The inducer assembly may include a cavity. The inducer assembly may also include an inducer in fluid communication with the cavity. Moreover, the inducer assembly may include at least one guide vane disposed within the cavity.
    Type: Grant
    Filed: November 5, 2012
    Date of Patent: September 13, 2016
    Assignee: General Electric Company
    Inventors: Richard William Johnson, David Martin Johnson, Bradley James Miller, Mitchell Merrill
  • Patent number: 9440244
    Abstract: The present invention relates to a centrifuge rotor, in particular a laboratory centrifuge rotor, including a rotor body, wherein the rotor body at least partially includes a porous metal or a porous metal alloy and an armoring located radially outside with respect to the rotation axis of the rotor body is provided.
    Type: Grant
    Filed: July 11, 2012
    Date of Patent: September 13, 2016
    Assignee: EPPENDORF AG
    Inventors: Matthias Schmidt, Steffen Arnold, Fritz Peter Schulze, Rajko Bittner, Stefan Boenisch
  • Patent number: 9435206
    Abstract: A system includes an inducer assembly configured to receive a fluid flow from compressor fluid source and to turn the fluid flow in a substantially circumferential direction into the exit cavity. The inducer assembly includes multiple flow passages. Each flow passage includes an inlet configured to receive the fluid flow and an outlet configured to discharge the fluid flow into the exit cavity, and each flow passage is defined by a first wall portion and a second wall portion extending between the inlet and the outlet. The first wall portion includes a first surface adjacent the outlet that extends into the exit cavity.
    Type: Grant
    Filed: September 11, 2012
    Date of Patent: September 6, 2016
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Richard William Johnson, Bradley James Miller, David Martin Johnson
  • Patent number: 9438080
    Abstract: An electric machine includes an end frame having a shaft bore extending therethrough. The end frame includes a first side and a second side. A shaft extends through the shaft bore. A bearing is supported by the end frame and is coupled to the shaft to support the shaft for rotation about a longitudinal axis. A first seal is fixedly attached to the end frame and includes an internal bore that is sized to cooperate with the shaft to form a seal point therebetween. The first seal is disposed on the first side of the end frame. A second seal is fixedly attached to the second side of the end frame. The second seal includes a movable portion in direct contact with the shaft to define a second seal point. The first seal point is on a first side of the bearing and the second seal point is on a second side of the bearing.
    Type: Grant
    Filed: March 8, 2013
    Date of Patent: September 6, 2016
    Assignee: Regal Beloit America, Inc.
    Inventor: Joseph S. Minogue
  • Patent number: 9416877
    Abstract: A cooling device for cooling of a seal fixed in a non-rotatable member and with a circumferential contact surface on a rotating member. A closed ring-formed chamber is arranged in the rotating member radially inside of the seal. The chamber contains an amount of cooling medium which at normal rotating operation is both liquid and gaseous, such that the liquid cooling medium which by centrifugal forces is pressed towards the outer wall of the chamber is evaporated from the heat generated by the seal, and where a cooling member is arranged on the rotating member to cool an area radially inside of the chamber, such that the gaseous cooling medium is condensed from the cooling effect of the cooling member. The invention also relates to a centrifugal separator comprising such a cooling device.
    Type: Grant
    Filed: June 11, 2010
    Date of Patent: August 16, 2016
    Assignee: Alfa Laval Corporate AB
    Inventors: Peter Hagqvist, Kjell Klintenstedt
  • Patent number: 9394915
    Abstract: A seal land for a gas turbine engine can include a seal body that can extend between a leading edge portion, a trailing edge portion, a radially outer surface and a radially inner surface. A notch can extend at least partially through the seal body between the radially outer surface and the radially inner surface.
    Type: Grant
    Filed: June 4, 2012
    Date of Patent: July 19, 2016
    Assignee: United Technologies Corporation
    Inventors: Amy M. Gordon, Jonathan J. Jakiel, Jonathan P. Burt, Steven D. Porter
  • Patent number: 9359875
    Abstract: The present invention relates to an artificial lift tool for being introduced in a wellbore or a casing and submerged in well fluid. The artificial lift tool extends in a longitudinal direction from a top end adapted to be connected to a wireline to a bottom end. The tool comprises a motor unit and a pump unit. Furthermore, invention relates to a production well wherein the artificial lift tool is submerged in a well fluid; to the use of the artificial lift tool for providing artificial lift in a well; and to a method for providing artificial lift in a well.
    Type: Grant
    Filed: December 29, 2011
    Date of Patent: June 7, 2016
    Assignee: WELLTEC A/S
    Inventor: Jørgen Hallundbæk
  • Patent number: 9197115
    Abstract: Embodiments of the invention provide an electric machine module including an electric machine. The electric machine includes a rotor and a stator assembly, and an output shaft having a longitudinal axis that is circumscribed by a portion of the rotor. The output shaft may comprise an output shaft channel and the rotor may include a rotor channel, and the rotor and the output shaft channels may be in fluid communication. The machine further includes a coolant jacket at least partially within a sleeve member that circumscribes at least a portion of the stator assembly, and at least one pump mounted generally concentrically with respect to the output shaft, that is in fluid communication with the coolant jacket. Some embodiments of the electric machine module include coupling to a fluid system that is configured and arranged to transport fluid, such as the coolant, throughout the fluid system.
    Type: Grant
    Filed: January 28, 2013
    Date of Patent: November 24, 2015
    Assignee: REMY TECHNOLOGIES, LLC
    Inventors: Larry Kubes, Thomas Bockelmann, Csaba Vari
  • Patent number: 9175690
    Abstract: A compressor is disclosed, which has an inflow channel for guiding a compression medium into a compressor housing, a pressure chamber formed within the compressor housing, and a liner segment with nozzles that transport the compression medium from the pressure chamber to a rotor. The nozzles are formed in the liner segment as a plurality of nozzles arranged in a group in fan-like manner.
    Type: Grant
    Filed: October 16, 2009
    Date of Patent: November 3, 2015
    Assignee: MTU AERO ENGINES GmbH
    Inventors: Gottfried Schütz, Sven-J. Hiller, Yves Burgold
  • Patent number: 9163515
    Abstract: A gas turbine arrangement and a method of operating are provided. The turbine includes an annulus, axially delimited between a rotor unit, and at least one stationary component. Cooling medium outlet openings, lead into the annulus, from the stationary component. The cooling medium flows into cooling medium inlet openings, in the rotor unit in a flow direction, which propagates through the annulus. At least one inner cavity, radially to the annulus, is delimited by the rotor unit and by the stationary component. The inner cavity is pressurized with a purging gas, and is fluidically connected to the annulus. The stationary component and the rotor unit include a constriction by which the inner cavity is separated from the radially outer annulus and via which the inner cavity is fluidically connected to the radially outer annulus. Flow guides, fastened on the stationary component on one side, project into the constriction.
    Type: Grant
    Filed: November 11, 2011
    Date of Patent: October 20, 2015
    Assignee: ALSTOM TECHNOLOGY LTD
    Inventors: Ulrich Robert Steiger, Sascha Justl
  • Patent number: 9145786
    Abstract: A method for reducing clearance flow in a channel between a bucket and an enclosure of a turbine. The method includes separating a single flow in the channel into a first flow and a second flow and directing the second flow radially inward toward the bucket so that the second flow rejoins with the first flow to increase total flow onto the bucket. A turbine includes an inner casing, a rotatable shaft positioned axially within the inner casing, a plurality of buckets connected to the shaft, a first tooth projecting radially inward from and connected to the inner casing, wherein the first tooth and at least one bucket form a first fluidic channel therebetween and a second tooth connected to and in parallel with the first tooth form a radial fluidic channel. The axial fluidic channel is in communication with the radial fluidic channel to form a second fluidic channel.
    Type: Grant
    Filed: April 17, 2012
    Date of Patent: September 29, 2015
    Assignee: General Electric Company
    Inventor: Yu Wang
  • Publication number: 20150147157
    Abstract: A journal configured to be driven in rotation in a housing of a turbine engine, or for an aircraft, the journal including: a circumferential main body including plural ventilation openings configured to allow plural axial airflows to circulate from upstream to downstream in the turbine engine, two consecutive ventilation openings being connected by a connecting segment, and a circumferential ring for recovering a flow of lubrication oil, which ring is rigidly connected to the main body and is radially inside the ventilation openings, the recovery ring including plural radial discharge openings for allowing plural radial flows of oil to be discharged towards the outside, each discharge opening being radially aligned with a connecting segment of the main body to allow each flow of oil to be discharged between the airflows.
    Type: Application
    Filed: June 12, 2013
    Publication date: May 28, 2015
    Applicant: SNECMA
    Inventors: Eddy Stephane Joel Fontanel, Giuliana Elisa Rossi, Philippe Pierre Vincent Bouiller, Emmanuel Da Costa, Julien Foll
  • Patent number: 9004856
    Abstract: An inlet connection piece for an axial compressor, particularly for a turbocompressor, includes an inlet housing (1) in which is arranged a bearing housing (2) with a bearing (3), particularly a radial and/or axial bearing, for a rotor. The bearing housing (2) is connected to the inlet housing (1) by an inlet strut (4) which is connected to the inlet housing in a front cross section. The center of the bearing (3) is arranged axially in the flow direction of a fluid to be compressed behind the area center of the front cross section by at least 0.1-times, particularly at least 0.15-times, particularly at least 0.2-times, particularly at least 0.25-times, the chord length of the front cross section. In addition or alternatively, a fluid passage (5, 6) is formed in the inlet strut (4), and at least portions of this fluid passage (5, 6) form an acute angle with a normal plane relative to the longitudinal axis of the inlet connection piece.
    Type: Grant
    Filed: November 3, 2008
    Date of Patent: April 14, 2015
    Assignee: MAN Diesel & Turbo SE
    Inventors: Christoph Lange, Henning Ressing, Fikri Aynacioglu, Dirk Anding, Karl-Heinz Dreyer
  • 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