Including Heat Insulation Or Exchange Means (e.g., Fins, Lagging, Etc.) Patents (Class 415/177)
  • Patent number: 11015534
    Abstract: A thermal management system includes a first heat source assembly including a first heat source exchanger, a first thermal fluid inlet line extending to the first heat source exchanger, and a first thermal fluid outlet line extending from the first heat source exchanger; a second heat source assembly including a second heat source exchanger, a second thermal fluid inlet line extending to the second heat source exchanger, and second a thermal fluid outlet line extending from the second heat source exchanger; a shared assembly including a thermal fluid line and a heat sink exchanger, the shared assembly defining an upstream junction in fluid communication with the first thermal fluid outlet line and second thermal fluid outlet line and a downstream junction in fluid communication with the first thermal fluid inlet line and second thermal fluid inlet line; and a controller configured to selectively fluidly connect the first heat source assembly or the second heat source assembly to the shared assembly.
    Type: Grant
    Filed: November 28, 2018
    Date of Patent: May 25, 2021
    Inventors: Justin Paul Smith, Brandon Wayne Miller, Daniel Alan Niergarth
  • Patent number: 10954815
    Abstract: Divided baffles for a gas turbine engines are provided. The divided baffles include a baffle body having a first end and a second end, at least one divider located within the baffle body and extending from the first end to the second end arranged to divide an interior of the baffle body into two or more feed cavities, at least one cap arranged at the first end to bound a first feed cavity of the two or more feed cavities, and at least one cap arranged at the second end to bound a second feed cavity of the two or more feed cavities.
    Type: Grant
    Filed: October 1, 2019
    Date of Patent: March 23, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Dominic J. Mongillo, Jr., Ricardo Trindade, Nicholas M. LoRicco
  • Patent number: 10947993
    Abstract: Embodiments are generally provided of a gas turbine engine including a rotor assembly comprising a shaft extended along a longitudinal direction, in which a compressor rotor and a turbine rotor are each coupled to the shaft; a casing surrounding the rotor assembly, in which the casing defines a first opening radially outward of the compressor rotor, the turbine rotor, or both, and a second opening radially outward of the compressor rotor, the turbine rotor, or both; a first manifold assembly coupled to the casing at the first opening; a second manifold assembly coupled to the casing at the second opening, in which the first manifold, the casing, and the second manifold together define a thermal circuit in thermal communication with the rotor assembly; and a fluid flow device in fluid communication with the first manifold assembly, in which the fluid flow device provides a flow of fluid to the first manifold assembly and through the thermal circuit, and further wherein the flow of fluid egresses the thermal ci
    Type: Grant
    Filed: November 27, 2017
    Date of Patent: March 16, 2021
    Assignee: General Electric Company
    Inventors: Kudum Shinde, Praveen Sharma, Shashank Suresh Puranik, Shivam Mittal, Charles Stanley Orkiszewski, Carl Lawrence MacMahon, Anthony Michael Metz, Brian Drummond
  • Patent number: 10935007
    Abstract: A geothermal turbine includes: a rotor; a casing which houses the rotor; a plurality of rotor blades disposed around the rotor; a plurality of stationary vanes supported on the casing; at least one seal portion disposed in a gap between the rotor and the casing at an upstream side of a first-stage rotor blade of the plurality of rotor blades so as to seal leakage steam which flows out inward in a radial direction of the rotor from between a first-stage stationary vane of the plurality of stationary vanes and the first-stage rotor blade; and a steam passage configured to extract a part of steam after passing the first-stage stationary vane and discharge the part of steam to the gap through an interior of the first-stage stationary vane.
    Type: Grant
    Filed: December 19, 2017
    Date of Patent: March 2, 2021
    Assignee: MITSUBISHI POWER, LTD.
    Inventors: Ryo Takata, Mitsuyoshi Tsuchiya, Yu Shibata
  • Patent number: 10927698
    Abstract: A turbocharger includes a variable-nozzle cartridge having a nozzle ring that supports an array of variable vanes in the turbine nozzle. A heat shroud and spring assembly is disposed in a space bounded between the turbine wheel, the nozzle ring, and the center bearing housing of the turbocharger. The heat shroud and spring assembly includes discretely formed heat shroud and spring components configured as annular non-planar disk-shaped parts. The heat shroud and spring are in contact with each other at their radially inner and radially outer peripheral regions, but are spaced apart between those peripheral regions, thereby creating a sealed-off dead space between them. The dead space can significantly reduce the maximum temperature of the spring, relative to arrangements having a single shroud or having dual shrouds with no dead space between them.
    Type: Grant
    Filed: January 10, 2019
    Date of Patent: February 23, 2021
    Assignee: Garrett Transportation I Inc.
    Inventors: Vit Micanek, Miroslav Protiva, Lucie Kovarova
  • Patent number: 10920595
    Abstract: The present disclosure generally relates to turbine engine components having multiple controlled metallic grain orientations. In general, the primary grain orientation is aligned substantially perpendicular to the longitudinal axis of the turbine engine component while the secondary grain orientation is aligned substantially parallel to the longitudinal axis. Such controlled grain orientations provide the blades and vanes with increased strength to withstand the thermal-mechanical stresses of the turbine operation. The disclosure also relates to turbines having these fortified components, and methods of manufacturing the components.
    Type: Grant
    Filed: January 13, 2017
    Date of Patent: February 16, 2021
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Narendra Digamber Joshi, Nicholas Joseph Kray, Samar Jyoti Kalita, Paul Marsland, Wayne Spence
  • Patent number: 10890080
    Abstract: A seal plate for a gas turbine engine includes an annular wall provided about an axis and extending between first and second ends that are radially spaced from one another with respect to the axis. The first end includes an axially extending pilot. The second end includes an axially extending flange and an adjacent annular seal seat. The wall includes a portion between the first and second ends that extend substantially in the axial direction and is configured to permit the second end to move axially relative to the first end in response to thermal growth.
    Type: Grant
    Filed: February 22, 2019
    Date of Patent: January 12, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Matthew Budnick, Conway Chuong
  • Patent number: 10844742
    Abstract: A heat shield (100) and method for assembling such is disclosed. The heat shield (100) may comprise an outer wall (122) and an inner wall (124). The outer wall (122) includes a first member (130), a flange (132) extending outward from the first member (130) and a first inner edge (134). The first member (130) extends from the flange (132) to the first inner edge (134). The inner wall (124) includes a second member (140), a rim (142) extending outward from the second member (140) and a second inner edge (144). The second member (140) extends from the rim (142) to the second inner edge (144). The inner wall (124) is spaced apart from the outer wall (122), the first and second edges form an air gap (146) between them, and the inner wall (124) and the outer wall (122) form a cavity (148).
    Type: Grant
    Filed: April 18, 2016
    Date of Patent: November 24, 2020
    Assignee: BorgWarner Inc.
    Inventors: Jonathan Williams, Raj Chandramohanan, Robert Race
  • Patent number: 10704555
    Abstract: The invention provides a stator-side member which is arranged in a vacuum pump and which, without the provision of a heat insulation material, prevents the deposition of products at the lower side of a threaded groove pump unit, with this lower side being an area of high pressure where the deposition of products (deposits) occurs easily, and also provides a vacuum pump equipped with this stator-side member. A threaded groove spacer configured to have a coefficient of thermal conductivity lower than a predetermined value is arranged in a vacuum pump equipped with a threaded groove pump unit. (1) The threaded groove spacer is manufactured from a material having a coefficient of thermal conductivity lower than that of a member which opposes or comes into contact with the threaded groove spacer.
    Type: Grant
    Filed: August 26, 2013
    Date of Patent: July 7, 2020
    Assignee: Edwards Japan Limited
    Inventors: Yoshiyuki Sakaguchi, Akihiro Ito, Yoshinobu Ohtachi, Yasushi Maejima, Tsutomu Takaada
  • Patent number: 10619852
    Abstract: According to one embodiment, a heat shield panel for a combustor of a gas turbine engine is provided. The heat shield comprising: a panel body having a first surface configured to be oriented toward a combustion zone of a combustor, and a second surface opposite the first surface, the second surface being configured to be oriented toward a combustor liner of the combustor; a plurality of first pin fins projecting from the second surface of the panel body, wherein each of the plurality of first pin fins has a rounded top opposite the second surface; and one or more second pin fins projecting from the second surface of the panel body, wherein each of the one or more second pin fins has a flat top opposite the second surface.
    Type: Grant
    Filed: August 25, 2017
    Date of Patent: April 14, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Steven D. Porter, John W. Mubeezi
  • Patent number: 10615667
    Abstract: Provided is a rotary electric machine in which cooling efficiency can be improved. The rotary electric machine includes a first refrigerant passage through which refrigerant passes from the shaft to the rotor core, wherein the rotor core includes a second refrigerant passage through which the refrigerant having passed through the first refrigerant passage passes, wherein the insulator includes: a base portion; a radially inner protruding portion, which is formed on a radially inner side of the base portion, and a radially outer protruding portion, which is formed on a radially outer side of the base portion, wherein the radially inner protruding portion has a first through-hole penetrating therethrough in a radial direction, and wherein the refrigerant having passed through the second refrigerant passage passes through the first through-hole to travel to the stator coil end portion.
    Type: Grant
    Filed: April 27, 2017
    Date of Patent: April 7, 2020
    Assignee: MITSUBISHI ELECTRIC CORPORATION
    Inventors: Yusuke Kimoto, Yoshiaki Kitta
  • Patent number: 10598031
    Abstract: A turbine rotor is fitted to a turbomachine and includes disks each containing a coupling portion with recesses each holding a root of a blade, and coupled to one another by a first annular ferrule attached to one of them close to the recesses, and second rotationally coupled ferrules, which are respectively coupled radially to the disks, which each consists of at least two semi-annular sectors, and which form with the associated disk a space which communicates with the recesses of the coupling portion of this latter disk. In addition, each first ferrule includes through-holes enabling air to enter this space, and then the recesses, intended to cool the coupling portion which couples its disk and the blade roots.
    Type: Grant
    Filed: September 8, 2017
    Date of Patent: March 24, 2020
    Assignee: SAFRAN AIRCTAFT ENGINES
    Inventors: Stéphane Pierre Guillaume Blanchard, Joao Antonio Amorim, Maxime Aurélien Rotenberg, Nicolas Xavier Trappier
  • Patent number: 10590955
    Abstract: A turbo-molecular pump comprises a cylindrical rotor to be rotatably driven by a motor; a cylindrical stator provided corresponding to the rotor; a heater configured to elevate a temperature of the stator to a target temperature; a temperature sensor configured to detect the temperature of the stator; and a control section. A rotation start command is input after start of energization of the heater, the control section stops rotary driving of the rotor at a rated rotation speed until the temperature of the stator reaches a predetermined temperature set lower than the target temperature and begins the rotary driving at the rated rotation speed when the temperature of the stator exceeds the predetermined temperature.
    Type: Grant
    Filed: February 23, 2017
    Date of Patent: March 17, 2020
    Assignee: Shimadzu Corporation
    Inventor: Nobuhiko Moriyama
  • Patent number: 10508548
    Abstract: An airfoil assembly for a turbine engine can comprise a platform having first and second opposing surfaces, an airfoil extending from the first surface, a base extending from the second surface, and a platform cooling circuit including a feed tube, a first branch, a second branch, and a flow divider.
    Type: Grant
    Filed: April 7, 2017
    Date of Patent: December 17, 2019
    Assignee: General Electric Company
    Inventors: James Michael Hoffman, Weston Nolan Dooley, Aaron Ezekiel Smith, Steven Robert Brassfield
  • Patent number: 10480347
    Abstract: Divided baffles for a gas turbine engines are provided. The divided baffles include a baffle body having a first end and a second end, at least one divider located within the baffle body and extending from the first end to the second end arranged to divide an interior of the baffle body into two or more feed cavities, at least one cap arranged at the first end to bound a first feed cavity of the two or more feed cavities, and at least one cap arranged at the second end to bound a second feed cavity of the two or more feed cavities.
    Type: Grant
    Filed: January 18, 2018
    Date of Patent: November 19, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Dominic J. Mongillo, Jr., Ricardo Trindade, Nicholas M. LoRicco
  • Patent number: 10443445
    Abstract: A method for manufacturing a turbine casing part having a bearing chamber system including a shell (1) and at least one bearing receptacle (2) and further having a protective heat shield (30) that at least partially encompasses the shell (1) radially outwardly, the protective heat shield (30) being additively manufactured integrally with the bearing chamber system by selectively solidifying layer-by-layer a feedstock material (5) is provided.
    Type: Grant
    Filed: March 25, 2016
    Date of Patent: October 15, 2019
    Assignee: MTU Aero Engines AG
    Inventors: Christian Liebl, Richard Scharl, Alexander Buck, Daniel Kirchner, Thomas Hess
  • Patent number: 10371005
    Abstract: A heat shield assembly for a gas turbine engine includes a first heat shield ply assembly defined about an axis; a second heat shield ply assembly defined about the axis, the second heat shield ply assembly receivable at least partially over the first heat shield assembly and a band clamp mounted to the second heat shield assembly to circumferentially retain the first heat shield ply assembly and the second heat shield ply assembly.
    Type: Grant
    Filed: July 20, 2016
    Date of Patent: August 6, 2019
    Assignee: United Technologies Corporation
    Inventors: Jeffrey D Ponchak, Mark J Rogers, James R Plante
  • Patent number: 10309415
    Abstract: An exhaust-gas turbocharger (1) having a compressor housing (2); a turbine housing (3); and a bearing housing (4) which has a compressor-side flange (5) and which has a turbine-housing-side flange (6). The turbine-housing-side flange (6) is produced from a material which corresponds in terms of its mechanical and thermal properties to the material of the turbine housing (2).
    Type: Grant
    Filed: May 21, 2012
    Date of Patent: June 4, 2019
    Assignee: BorgWarner Inc.
    Inventors: Robert Lingenauber, Frank Scherrer, Josef-Hans Hemer, Michael Fischer
  • Patent number: 10273812
    Abstract: An air supply system is configured to provide cooling air with reduced heat pickup to a turbine rotor of a gas turbine engine. The system comprises a first cooling passage extending between a hollow airfoil and an internal pipe extending through the airfoil. The airfoil extends through a hot gas path. A second cooling passage extends through the internal pipe. The coolant flowing through the second cooling passage is thermally isolated from the airfoil hot surface by the flow of coolant flowing through the first cooling passage. The first and second cooling passages have a common output flow to a rotor cavity of the turbine rotor where coolant flows from the first and second cooling passages combine according to a predetermined ratio.
    Type: Grant
    Filed: December 18, 2015
    Date of Patent: April 30, 2019
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Roger Huppe, Marc Tardif, Herve Turcotte
  • Patent number: 10240460
    Abstract: A gas turbine engine component includes an insulating coating that is adhered to a surface of the component that permits the component to operate at higher temperatures with reduced thermal stress. The coating can be selectively applied to one or more portions of a part feature where, in some embodiments, the part feature may include a portion that does not include the coating. The part feature can include recognized features of a component such as an interior surface of a hollow component, a back side of a blade track, a cooling hole passage, etc.
    Type: Grant
    Filed: December 18, 2013
    Date of Patent: March 26, 2019
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: David J. Thomas, Ted J. Freeman
  • Patent number: 10233777
    Abstract: A first stage vane arrangement having an array of first stage vanes and an array of frame segments and method for cooling frame segments of the first vane arrangement of a gas turbine are disclosed. The frame segments are designed for axially receiving aft ends of a combustor transition pieces. The first stage vanes include extended vanes, each vane having a leading section, a trailing edge, and an airfoil extending between an outer platform and an inner platform. The frame segments having an I-beam with an upper horizontal element, a lower horizontal element, and a vertical web. The vertical web having a downstream face facing towards a first stage of a turbine when installed in a gas turbine. The downstream face of the vertical web of at least one of the frame segments overlaps, at least partially, the leading section of at least one of the extended vanes.
    Type: Grant
    Filed: July 28, 2016
    Date of Patent: March 19, 2019
    Assignee: ANSALDO ENERGIA SWITZERLAND AG
    Inventors: Fabien Fleuriot, Hans-Christian Mathews, Andrey Chukin
  • Patent number: 10221864
    Abstract: A vacuum pump comprises a rotor shaft, which bears one or more rotor elements. The rotor shaft is driven by an electrical driver. A stator is arranged between the rotor elements. The rotor shaft is supported by bearings. The highly heat-generating components such as the driver and the stator are connected to a second housing part in particular by means of a support member. Heat-sensitive components such as the bearing are supported by means of a separate first housing part. The two housing parts can be kept at different temperatures, for example by means of separate cooling devices. Thus, the operating temperature of the in particular pressure-side bearing can be reduced, and therefore the service life can be extended.
    Type: Grant
    Filed: September 11, 2014
    Date of Patent: March 5, 2019
    Assignee: LEYBOLD GMBH
    Inventor: Rainer Hölzer
  • Patent number: 10161404
    Abstract: A turbo-molecular pump comprises: a pump rotor including rotor blades and a rotor cylindrical section; stationary blades facing the rotor blades; a cylindrical stator facing the rotor cylindrical section; a base housing the cylindrical stator; and a heating member for heating the cylindrical stator. An emissivity of an outer surface of the cylindrical stator and an emissivity of an outer surface of a member facing the cylindrical stator, the outer surface facing the cylindrical stator, are lower than the emissivity of outer surfaces of the rotor blades, the outer surfaces facing the stationary blades.
    Type: Grant
    Filed: May 22, 2015
    Date of Patent: December 25, 2018
    Assignee: SHIMADZU CORPORATION
    Inventors: Shingo Tsutsui, Tetsuya Tsubokawa
  • Patent number: 10094239
    Abstract: A vane assembly for a gas turbine engine is disclosed in this paper. The vane assembly includes an inner platform, an outer platform, and a ceramic-containing airfoil. The ceramic-containing airfoil extends from the inner platform to the outer platform. A reinforcement spar made from a metallic material extends from the inner platform to the outer platform through a hollow core of the ceramic-containing airfoil.
    Type: Grant
    Filed: September 29, 2015
    Date of Patent: October 9, 2018
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Ted J. Freeman, Bruce E. Varney, David J. Thomas, Jeffrey A. Walston
  • Patent number: 10018424
    Abstract: A heat exchanger has an outer shell enclosing an inner chamber and extending between a first inlet and a first outlet. The chamber receives a separating wall. The shell extends between axial ends, and generally along a helix. The helix is defined with the wall moving in a continuous manner along a first axial direction and with a circumferential component between the first inlet and the first outlet. A plurality of tubes extend through openings in the separating wall and generally along a helix. The plurality of tubes extend from a second inlet and a second outlet, and with the helix defined along the first axial direction and with a component in a circumferential direction. A method and a temperature control system are also disclosed.
    Type: Grant
    Filed: February 5, 2016
    Date of Patent: July 10, 2018
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Mark A. Zaffetti, Jeremy M. Strange
  • Patent number: 9988977
    Abstract: A turbocharger (10) includes a shaft (26) rotatably supported within a bearing housing (28), a turbine wheel (22) connected to the shaft (26), and a heat shield (150, 250) disposed between the turbine wheel (22) and the bearing housing (28). The heat shield (150, 250) includes surface features (80, 180) formed on at least one of a sidewall (57) portion thereof and a flange (63) portion thereof that locate the heat shield (150, 250) relative to the bearing housing (28) such that the heat shield (150, 250) is coaxial with the rotational axis of the shaft (26).
    Type: Grant
    Filed: September 30, 2015
    Date of Patent: June 5, 2018
    Assignee: BorgWarner Inc.
    Inventors: Jerud Crandall, Gordon Jenks, Michael Thayer
  • Patent number: 9938842
    Abstract: A cooling system for a turbomachine includes a vane having an outer diameter platform at one end and an inner diameter platform at another end opposite the outer diameter platform. The outer diameter platform includes outer diameter attachment structure operative to mount the vane to an outer diameter stationary structure. The inner diameter platform is operative to be disposed on an inner diameter stationary structure. The cooling system also includes an airfoil disposed between the outer diameter platform and the inner diameter platform and defining a first cross-passage. The first cross-passage defines a first outer diameter opening in the outer diameter platform. The first cross-passage defines a first inner diameter opening in the inner diameter platform such that a first leakage flow can pass through the vane from the inner diameter platform, through the airfoil, to the outer diameter platform, and into an outer diameter leakage path of the vane.
    Type: Grant
    Filed: January 20, 2015
    Date of Patent: April 10, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Brandon W. Spangler
  • Patent number: 9879594
    Abstract: A turbocharger is provided including a turbine housing having a gas inlet passage. A turbine wheel having a plurality of blades is arranged within the turbine housing. A nozzle ring is disposed around the turbine wheel and includes a plurality of vanes with flow channels being defined between the vanes that are in fluid communication the gas inlet passage and with the turbine wheel. A shroud is arranged in surrounding relation to at least a portion of the turbine wheel and in spaced relation from the turbine housing. The shroud is integrally formed with the nozzle ring such that the plurality of vanes extend away from the shroud.
    Type: Grant
    Filed: March 9, 2015
    Date of Patent: January 30, 2018
    Assignee: Caterpillar Inc.
    Inventors: Richard E. Annati, Matthew J. Frick, Robert Griffith
  • Patent number: 9869183
    Abstract: A rotor for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a rotor disk rotatable about an axis and a gas path wall coupled to and radially outward of the rotor disk. The gas path wall bounds a radially inward portion of a gas path. A plurality of rotor spokes are radially intermediate the rotor disk and the gas path wall. The plurality of rotor spokes is circumferentially spaced to define a plurality of cooling channels intermediate the rotor disk and the gas path wall. A thermal barrier coating is disposed on a surface of at least one of the plurality of cooling channels. A method of cooling a rotor assembly is also disclosed.
    Type: Grant
    Filed: July 15, 2015
    Date of Patent: January 16, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Gabriel L. Suciu, Brian D. Merry, James D. Hill, Wesley K. Lord
  • Patent number: 9863278
    Abstract: A support for carrying a tube for discharging oil-laden air from a turbine engine, the support including a radially inner annular portion for mounting around the tube, and fins that are inclined relative to the axial direction of the annular portion and relative to the radial plane, the radially outer periphery of each fin being for fastening to an exhaust cone of the turbine engine.
    Type: Grant
    Filed: November 4, 2013
    Date of Patent: January 9, 2018
    Assignee: SNECMA
    Inventors: Patrick Sultana, Boucif Bensalah, Yannick Durand, Olivier Renon
  • Patent number: 9850761
    Abstract: An airfoil assembly for a gas turbine engine is disclosed and includes a platform portion defining a portion of a gas flow path and a root portion for attachment of the turbine airfoil, the root portion including a bottom surface including a bottom area and a plurality of inlets that define a total inlet area as a ratio of the inlet area to the bottom area. An airfoil extends from the platform and including a plurality of cooling air passages in communication with the plurality of inlets.
    Type: Grant
    Filed: January 24, 2014
    Date of Patent: December 26, 2017
    Assignee: United Technologies Corporation
    Inventors: Seth J. Thomen, Wieslaw A. Chlus
  • Patent number: 9822799
    Abstract: An arrangement includes a vacuum pump having a rotor, and a drive unit for driving the rotor and having at least one magnetic interference field-generating component and at least one compensation coil for compensating the magnetic interference field generated by the at least one component.
    Type: Grant
    Filed: September 10, 2014
    Date of Patent: November 21, 2017
    Assignee: PFEIFFER VACUUM GMBH
    Inventor: Armin Conrad
  • Patent number: 9822783
    Abstract: A vacuum pump comprises a cylindrical rotor; a cylindrical stator which discharges gas in cooperation with the rotor; a base housing at least a part of the stator and having a through hole formed at a position facing an outer periphery of the stator; a heating member passing through the through hole from an atmosphere side to a vacuum side to have thermal contact with an outer peripheral surface of the stator to heat the stator; and an axial seal member which vacuum-seals a gap between the through hole and the heating member.
    Type: Grant
    Filed: May 22, 2015
    Date of Patent: November 21, 2017
    Assignee: SHIMADZU CORPORATION
    Inventor: Tetsuya Tsubokawa
  • Patent number: 9752506
    Abstract: A device for connecting a fixed turbine engine portion and a distributor foot of a turbine engine turbine is provided. The device includes a ring-shaped body adapted so as to be connected and secured to the fixed turbine engine portion, and two ring-shaped upstream and downstream brackets secured to the body, both brackets being adapted so as to clamp the foot of the distributor. At least one bracket is interrupted by forming an expansion or retraction slot, the slot allowing an expansion of the bracket tending to close the slot or retraction of the bracket tending to further open the slot, under the effect of a difference in internal temperatures of the device.
    Type: Grant
    Filed: October 1, 2014
    Date of Patent: September 5, 2017
    Assignee: SNECMA
    Inventors: Eric Schwartz, Fabien Garnier, Helene Condat, Renaud Gabriel Constant Royan, Patrick Joseph Marie Girard
  • Patent number: 9708916
    Abstract: A casted turbine bucket having at least one machined plenum including a plenum chamber and at least one plenum passage connected to a plenum inlet at a root portion of turbine bucket, and a method to feed cooling flow to the turbine bucket using the machined plenum that receives cooling flow from the root portion of the turbine bucket.
    Type: Grant
    Filed: July 18, 2014
    Date of Patent: July 18, 2017
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Xiuzhang James Zhang, Lisa DeBellis, Haiping Wang
  • Patent number: 9618012
    Abstract: A turbo-molecular pump comprises a rotor having rotor blades and a cylindrical section; stationary blades; a plurality of spacers; a stator arranged with a gap from the cylindrical section, a base; a spacer cooling section arranged between a lowest spacer of the stacked spacers and the base, the spacer cooling section having a first flow passage through which coolant flows; a heater for heating the stator; a temperature sensor for detecting a temperature of the stator; a base cooling section for cooling the base, the base cooling section having a second flow passage connected in series to the first flow passage; and a temperature controller for controlling circulation of coolant to the first flow passage and the second flow passage connected in series and energization of the heater to maintain the temperature of the stator at a predetermined temperature.
    Type: Grant
    Filed: December 31, 2014
    Date of Patent: April 11, 2017
    Assignee: Shimadzu Corporation
    Inventor: Shingo Tsutsui
  • Patent number: 9587517
    Abstract: A turbine shroud assembly or blade track assembly adapted to extend around a turbine wheel assembly is disclosed. The turbine shroud assembly includes a carrier and a blade track coupled to the carrier. The blade track is movable between a radially-inward position having a first inner diameter and a radially-outward position having a second inner diameter larger than the first inner diameter.
    Type: Grant
    Filed: November 24, 2015
    Date of Patent: March 7, 2017
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventors: Daniel K. Vetters, Joseph Doyle, Michael Jacquinto, Wesley Thibault
  • Patent number: 9556749
    Abstract: An exhaust gas housing for a gas turbine, in which an annular gas passage, through which exhaust gas discharges from the gas turbine to the outside, is formed by a concentric inner casing and an outer casing which concentrically encompasses the inner casing at a distance, wherein the inner casing and the outer casing are interconnected by a plurality of radial struts which extend through the gas passage and have in each case a leading edge and a trailing edge with regard to the exhaust gas flowing through the gas passage, and wherein the struts, the outer casing and the inner casing are equipped in each case with a heat-resistant lining towards the gas passage, wherein the lining of the struts is at least partially mechanically decoupled from the lining of the inner casing and/or of the outer casing for reducing thermal stresses on the periphery of the struts.
    Type: Grant
    Filed: December 5, 2012
    Date of Patent: January 31, 2017
    Assignee: GENERAL ELECTRIC TECHNOLOGY GMBH
    Inventors: Ernst Pauli, Mario Dombos, Andreas Kieninger, Joachim Krautzig
  • Patent number: 9382810
    Abstract: A system for removing heat from a gas turbine generally includes a plurality of stationary nozzles arranged in an annular array within the gas turbine. Each of the plurality of stationary nozzles may include a radially outer platform and a radially extending cooling passage. The radially extending cooling passage may have an inlet that extends generally axially and circumferentially across a portion of the radially outer platform. A closed loop cooling coil may extend continuously circumferentially around the radially outer platform of two or more of the plurality of stationary nozzles. The closed loop cooling coil may be disposed circumferentially across and outside of the inlet of the radially extending cooling passage of each of the two or more stationary nozzles, and a cooling medium may flow through the cooling coil and out of the gas turbine so as to remove heat from the gas turbine.
    Type: Grant
    Filed: July 27, 2012
    Date of Patent: July 5, 2016
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Benjamin Paul Lacy, Gregory Allan Crum, James William Vehr
  • Patent number: 9365296
    Abstract: A transfer tube including a tube member extends from a first end to a second end through an intermediate portion having an outer surface and an inner surface. The outer surface has an outside diameter. A flange is mounted at one of the first and second ends of the tube member. The flange includes a flange body extending from a first end portion to a second end portion through an intermediate section having an outer surface and an inner surface. The inner surface defines an inside diameter. The outside diameter of the tube member is between about 0.010-inch (0.0254-cm) and about 0.030-inch (0.0762-cm) smaller than the inside diameter of the flange.
    Type: Grant
    Filed: May 8, 2013
    Date of Patent: June 14, 2016
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Brian Cabello, William R. Fiske, Danielle Mansfield-Marcoux
  • Patent number: 9366367
    Abstract: A cooling tube includes a tube member extending from a first end to a second end through an intermediate portion having an outer surface and an inner surface. The outer surface has an outside diameter. A flange is mounted at one of the first and second ends of the tube member. The flange includes a flange body extending from a first end portion to a second end portion through an intermediate section having an outer surface and an inner surface. The inner surface defines an inside diameter. The outside diameter of the tube member is between about 0.010-inch (0.0254-cm) and about 0.030-inch (0.0762-cm) smaller than the inside diameter of the flange.
    Type: Grant
    Filed: May 8, 2013
    Date of Patent: June 14, 2016
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Danielle Mansfield-Marcoux, Brian Cabello, William R. Fiske
  • Patent number: 9328924
    Abstract: A first orifice on a first inner surface of a first annular zone of a forward-bounded annular combustor provides for injecting air forward and radially outwards thereinto, from a location aft of a fuel slinger/injector. A radial dimension of a first outer surface of the first annular zone exceeds that of a corresponding first inner surface. A radial dimension of a second outer surface of a second annular zone of the annular combustor—aft of the first annular zone—exceeds that of a corresponding second inner surface. The first and second outer surfaces, and the first and second inner surfaces, are respectively coupled by transitional outer and inner surfaces of an annular transition zone located therebetween. The radial dimensions of the transitional outer and inner surfaces at the junctions with the corresponding second surfaces exceed the corresponding radial dimensions at the junctions with the corresponding first surfaces.
    Type: Grant
    Filed: January 6, 2014
    Date of Patent: May 3, 2016
    Assignee: WILLIAMS INTERNATIONAL CO., LLC
    Inventors: Jamey J. Condevaux, Lisa M. Simpkins, John Sordyl
  • Patent number: 9303528
    Abstract: A thermal radiation shield comprises a first mounting base and a ring section. The first mounting base is disposed at a first axial end of the ring section for securing the shield ring section within a generally annular cavity defined at least in part by a hot fluid flow path boundary wall, and a radially adjacent and spaced apart cold fluid flow path boundary wall. The ring section is configured to substantially block a line of sight between the hot fluid flow path boundary wall and the cold fluid flow path boundary wall.
    Type: Grant
    Filed: July 6, 2012
    Date of Patent: April 5, 2016
    Assignee: United Technologies Corporation
    Inventors: Paul K. Sanchez, Jorge I. Farah
  • Patent number: 9284844
    Abstract: A component for a gas turbine engine includes a wall and a cooling hole extending through the wall. The wall has a first surface and a second surface. The cooling hole includes a metering section that extends from an inlet in the first surface of the wall to a transition, a diffusing section that extends from the transition to an outlet in the second surface of the wall, and a cusp on the transition.
    Type: Grant
    Filed: July 9, 2012
    Date of Patent: March 15, 2016
    Assignee: United Technologies Corporation
    Inventor: JinQuan Xu
  • Patent number: 9140139
    Abstract: A structural joint includes a first flange, a second flange and a fastener with a head and a shaft. The first flange extends out from a first component to a distal first flange end. The second flange extends out from a segmented second component to a distal second flange end. The second flange includes a first lateral flange segment that extends laterally to a first flange sidewall, and a second lateral flange segment that extends laterally to a second flange sidewall, which is engaged with the first flange sidewall. The head is encased in the second flange and extends laterally into the first flange sidewall and the second flange sidewall. The shaft extends longitudinally out from the second flange and through the first flange.
    Type: Grant
    Filed: December 1, 2011
    Date of Patent: September 22, 2015
    Assignee: United Technologies Corporation
    Inventor: Eric W. Malmborg
  • Patent number: 9097121
    Abstract: The invention relates to a turbine casing (1) of an exhaust-gas turbocharger (62), having an inlet connection piece (2) adjoined by a spiral (3), and having an outlet connection piece (4), characterized by an insulating device (5) for reducing the input of heat into the inlet connection piece (2), the spiral (3) and/or the outlet connection piece (4).
    Type: Grant
    Filed: October 22, 2010
    Date of Patent: August 4, 2015
    Assignee: BorgWarner Inc.
    Inventors: Volker Joergl, Timm Kiener, Thomas Kritzinger, Stefan Weiss, Sylvia Wuest
  • Patent number: 9057282
    Abstract: Embodiments of the invention can provide systems and methods for adjusting clearances in a turbine. According to one embodiment of the invention, there is disclosed a turbine system. The system may include one or more turbine blades; a turbine casing encompassing the one or more turbine blades; and a thermoelectric element disposed at least partially about the turbine casing, wherein the thermoelectric element expands or contracts the turbine casing by heating or cooling at least a portion of the turbine casing, thereby adjusting a clearance between the one or more turbine blades and the turbine casing.
    Type: Grant
    Filed: November 22, 2011
    Date of Patent: June 16, 2015
    Assignee: General Electric Company
    Inventors: Rahul J. Chillar, Erwing Calleros, Prabhakaran Saraswathi Rajesh, Ezio Pena, Nicolas Antoine, Jose-Quintino Da-Costa
  • Patent number: 9032752
    Abstract: A system configured to thermally regulate exhaust portions of a power plant system (e.g. steam turbine) is disclosed. In one embodiment, a system includes: a condenser adapted to connect to and thermally regulate exhaust portions of a steam turbine; and a cooling system operably connected to the condenser and adapted to supply a cooling fluid to the condenser, the cooling system including a solar absorption chiller adapted to adjust a temperature of the cooling fluid.
    Type: Grant
    Filed: January 19, 2012
    Date of Patent: May 19, 2015
    Assignee: General Electric Company
    Inventors: Scott Victor Hannula, Duncan George Watt
  • Patent number: 9033028
    Abstract: A heat dissipation module includes a centrifugal fan and a heat pipe. The centrifugal fan includes an outer housing, a heat dissipation fin array, a retaining wall, an impeller and a rotation-driving device. The outer housing includes an axial air inlet, an axial air outlet and a radial air outlet. The heat dissipation fin array is located at an inner wall of the radial air outlet. The retaining wall is located on a flat wall of the outer housing on which the axial air outlet is located. The retaining wall is in contact with an inner wall of an electronic device to collectively form a circulation channel so as to guide airflows output from the axial air outlet through the flat wall with which the heat dissipation fin array is aligned, and into the axial air inlet. The heat pipe is in contact with the heat dissipation fin array.
    Type: Grant
    Filed: July 3, 2013
    Date of Patent: May 19, 2015
    Assignee: QUANTA COMPUTER INC.
    Inventor: Che-Ming Wang
  • Publication number: 20150121877
    Abstract: To improve the exhaust heat recovery efficiency, a compressor includes a heat exchanger for cooling a gas, coolant, water, or oil heated by the compressor during compressor operation by heat exchange with a working fluid, for circulating the working fluid of a Rankine cycle. The Rankine cycle is implemented by the heat exchanger, an expander, a condenser, and a circulating pump to circulate the working fluid through the cycle.
    Type: Application
    Filed: January 6, 2015
    Publication date: May 7, 2015
    Inventor: Yuji KAMIYA