Patents Examined by Stephanie Cheng
  • Patent number: 10663170
    Abstract: A flow conditioner in a combustor of a gas turbine comprises a body and a flow conditioning portion configured to be placed in an air path providing air flow to a combustion chamber, the flow conditioning portion including a plurality of holes tuned to a damping frequency to dampen a pressure fluctuation caused by combustion dynamics from the combustion chamber.
    Type: Grant
    Filed: January 19, 2017
    Date of Patent: May 26, 2020
    Assignee: Doosan Heavy Industries Construction Co., Ltd.
    Inventors: Esam Abu-Irshaid, Kevin Spence
  • Patent number: 10663169
    Abstract: A cylinder for a combustor includes a cylindrical member, a first cooling passage defined in the cylindrical member and a second cooling passage defined in the cylindrical member, and a supply port extender. The first cooling passage includes a supply port that opens to an outer peripheral surface of the cylindrical member. The second cooling passage includes a discharge port that opens to the outer peripheral surface of the cylindrical member downstream of the supply port. The supply port extender includes a first wall that is disposed between the supply port and the discharge port and extends away from the outer peripheral surface of the cylindrical member and a second wall that is disposed upstream of the supply port and extends away from the outer peripheral surface of the cylindrical member.
    Type: Grant
    Filed: July 22, 2015
    Date of Patent: May 26, 2020
    Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.
    Inventors: Satoshi Mizukami, Satoshi Tanimura, Tetsu Konishi, Masaki Mitani, Taiki Kinoshita, Yoshiaki Yamaguchi, Takaaki Hase, Hiroshi Makigano, Hikaru Kurosaki
  • Patent number: 10626798
    Abstract: A thermal energy exchange system for cooling air of a gas turbine engine includes a heat exchanger located at a diffuser of the gas turbine engine. The diffuser is positioned axially between a compressor and a combustor of the gas turbine engine. A fuel source is operably connected to the heat exchanger to direct a flow of fuel through the heat exchanger via a fuel pipe and toward a fuel nozzle of the combustor. An airflow inlet directs a cooling airflow through the heat exchanger to reduce an airflow temperature via thermal energy exchange between the cooling airflow and the flow of fuel. An airflow outlet directs the cooling airflow from the heat exchanger toward one or more of components of the turbine to cool the one or more components.
    Type: Grant
    Filed: December 9, 2015
    Date of Patent: April 21, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: James D. Hill, Steven J. Laporte, Wendell V. Twelves, Jr., Stephen K. Kramer, Simon Pickford
  • Patent number: 10612405
    Abstract: A system for retaining stators and reducing air leakage in a gas turbine engine having an axis includes a stator having an inner platform, an outer platform, a low pressure side, a high pressure side, and at least one foot, and designed to turn air. The system also includes a case positioned radially outward from the stator and having at least one recess designed to interface with the at least one foot to resist movement of the stator relative to the case. The system also includes a bladder positioned between the outer platform of the stator and the case and designed to receive pressurized fluid having a greater pressure than ambient pressures experienced at the low pressure side of the stator and to further resist movement of the stator relative to the case in response to receiving the pressurized fluid.
    Type: Grant
    Filed: January 13, 2017
    Date of Patent: April 7, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Anthony R. Bifulco
  • Patent number: 10605168
    Abstract: The present disclosure is directed to a gas turbine engine defining a longitudinal direction, a radial direction extended from an axial centerline, and a circumferential direction. The gas turbine engine includes a compressor section, a combustion section, and a turbine section in serial flow arrangement along the longitudinal direction. The gas turbine engine includes a low speed turbine rotor including a hub extended along the longitudinal direction and radially within the combustion section; a high speed turbine rotor including a high pressure (HP) shaft coupling the high speed turbine rotor to a HP compressor in the compressor section; and a first turbine bearing disposed radially between the hub of the low speed turbine rotor and the HP shaft. The HP shaft extends along the longitudinal direction and radially within the hub of the low speed turbine rotor. The high speed turbine rotor defines a turbine cooling conduit extended within the high speed turbine rotor.
    Type: Grant
    Filed: May 25, 2017
    Date of Patent: March 31, 2020
    Assignee: General Electric Company
    Inventors: Alan Roy Stuart, Jeffrey Donald Clements, Richard Schmidt, Thomas Ory Moniz
  • Patent number: 10598047
    Abstract: A bowed rotor prevention system for a gas turbine engine includes a core turning motor operable to drive rotation of an engine core of the gas turbine engine. The bowed rotor prevention system also includes an auxiliary electric motor control operable to control the core turning motor to drive rotation of the engine core using electric power while a full authority digital engine control that controls operation of the gas turbine engine is either depowered or in a power state that is less than a power level used by the full authority digital engine control in flight operation.
    Type: Grant
    Filed: February 28, 2017
    Date of Patent: March 24, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Jesse W. Clauson, Frederick M. Schwarz
  • Patent number: 10584643
    Abstract: A method for operating a supply assembly configured for supplying fuel gas and an inert purge media to a gas turbine combustor, the method including supplying fuel gas in a fuel gas circuit with an upper flow rate; reducing the fuel gas flow rate in the fuel gas circuit from the upper flow rate to a lower flow rate; stopping the supply of the fuel gas in the fuel gas circuit; and starting the supply of the inert purge media in the inert purge media circuit, wherein the starting is performed before the stopping to have a temporary parallel supply of fuel gas and of inert purge media to a fuel distribution system.
    Type: Grant
    Filed: December 27, 2017
    Date of Patent: March 10, 2020
    Assignee: Ansaldo Energia Switzerland AG
    Inventors: Susanne Renate Schell, Martin Liebau
  • Patent number: 10563582
    Abstract: A heat exchanger array includes a first row of heat exchangers, a second row of heat exchangers, and side curtains. The first row heat exchangers are spaced apart to define first gaps. The second row heat exchangers are spaced apart to define second gaps and are positioned downstream of and staggered from the first row heat exchangers such that the second row heat exchangers are aligned with the first gaps and the first row heat exchangers are aligned with the second gaps. Each side curtain is in close proximity to a first row heat exchanger and a second row heat exchanger. The side curtains define a neck region upstream of and aligned with each first row heat exchanger and each second row heat exchanger. Each neck region has a neck area that is less than a frontal area of the heat exchanger with which it is aligned.
    Type: Grant
    Filed: January 19, 2016
    Date of Patent: February 18, 2020
    Assignee: United Technologies Corporation
    Inventors: Paul W. Duesler, Frederick M. Schwarz
  • Patent number: 10539076
    Abstract: A self-contained lubrication fluid circulation system for use with a gas turbine engine defining a core air flowpath includes a sump configured to collect lubrication fluid and a heat source coupled in fluid communication with the sump and configured to transfer heat to the lubrication fluid. The system also includes a heat sink positioned within the sump and coupled in fluid communication with the heat source. A lubrication fluid conduit of the system is configured to channel the lubrication fluid between the heat source and the heat sink, wherein the lubrication fluid conduit is positioned entirely within the sump.
    Type: Grant
    Filed: November 10, 2015
    Date of Patent: January 21, 2020
    Assignee: General Electric Company
    Inventors: Daniel Alan Niergarth, Brandon Wayne Miller, Kyle Robert Snow, Christopher James Kroger
  • Patent number: 10533519
    Abstract: Aspects are directed to a system associated with a thrust reverser of an aircraft, comprising: a blocker door and a fan case, where when the thrust reverser is stowed the blocker door is stowed at least in part radially outboard of the fan case. Aspects include a thrust reverser system comprising: a fixed structure, a translating sleeve configured to translate relative to the fixed structure, at least one blocker door pivotally mounted to the translating sleeve, and a rod coupled to the fixed structure and to the at least one blocker door, where during a first phase of thrust reverser deployment the blocker door translates with the translating sleeve when the translating sleeve is translating toward its deployed position and does not rotate, and during a second phase following the first phase, the blocker door pivots relative to the translating sleeve from a stowed position to a deployed position.
    Type: Grant
    Filed: January 13, 2016
    Date of Patent: January 14, 2020
    Assignee: Rohr, Inc.
    Inventor: Timothy Gormley
  • Patent number: 10530159
    Abstract: A method for providing negative control power for an electrical supply and/or transmission network by means of the operation of a gas turbine, includes the following steps: a dynamo-electric machine of the gas turbine is supplied with electric power for motor operation from the supply and/or transmission network; the electrical input power is regulated or controlled by the motor operation on the basis of a network signal from the supply and/or transmission network to which the gas turbine is connected; and an operating parameter of the gas turbine for motor operation is altered as a result of this regulation or control for the purpose of deliberately increasing the electrical input power from the supply and/or transmission network.
    Type: Grant
    Filed: February 27, 2014
    Date of Patent: January 7, 2020
    Assignee: SIEMENS AKTIENGESELLSCHAFT
    Inventors: G√ľnther Ebner, Uwe Lenk
  • Patent number: 10519897
    Abstract: A divergent flap includes a hinge joint to connect the divergent flap to a convergent flap, a plow structure, a first wall, a second wall, and two side walls. The plow structure is at a plow end of the flap opposite the hinge joint. The first wall and the second wall each extend from the hinge joint to the plow end. The second wall is spaced apart from the first wall by the two side walls to form at least one cooling channel extending between the hinge joint and the plow end. The divergent flap is integrally formed in layer-by-layer fashion as a single piece.
    Type: Grant
    Filed: January 21, 2015
    Date of Patent: December 31, 2019
    Assignee: United Technologies Corporation
    Inventor: Meggan Harris
  • Patent number: 10519867
    Abstract: An integrated inlet particle separator (IPS) blower/engine starter including a housing having an inlet and an outlet. A turbine member is rotatably supported in the housing. A geared member operatively connected to the turbine member extends outward from the housing. The integrated IPS blower/engine starter is operable in a first configuration receiving a first fluid flow to rotate the geared member and in a second configuration generating a fluid flow through powered rotation of the geared member.
    Type: Grant
    Filed: September 27, 2017
    Date of Patent: December 31, 2019
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: Joseph Lawrence Simonetti, Andrew G. Keith
  • Patent number: 10508813
    Abstract: A plurality of gas turbine combustors having a cross fire tube assembly that connects adjacent combustors. The combustors include combustion chambers having annular combustion air passages on outer peripheries thereof. The cross fire tube assembly has a dual pipe configuration including an inner tube that connects the combustion chambers of the adjacent combustors and an outer tube that covers therein the inner tube and connects the combustion air passages of the adjacent combustors. The cross fire tube assembly further has openings disposed between the inner tube and the outer tube of outer peripheral partition walls of the combustion air passages that are connected with the outer tube of the cross fire tube assembly centering on the inner tube. The openings allow combustion air to flow in areas upstream and downstream of the inner tube with respect to a flow of the combustion air flowing through the combustion air passages.
    Type: Grant
    Filed: January 27, 2017
    Date of Patent: December 17, 2019
    Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.
    Inventor: Hirofumi Okazaki
  • Patent number: 10494999
    Abstract: A gas turbine engine for an aircraft includes a compressor, a combustion chamber, and a turbine having at least one stator, and at least one rotor. Each stator and rotor is formed by a plurality of blades, a fluid channel is formed between two consecutive blades, and each blade has two opposing surfaces. The compressor is in fluid communication with a first group of stator channels, and the combustion chamber is in fluid communication with a second group of stator channels, such that heat exchange can be performed through two opposing surfaces of at least one stator blade. The outer and the inner walls define a duct for the passage of the heated fluid through the rotor blades, and the outer wall is also arranged for directing the compressed air towards the combustion chamber.
    Type: Grant
    Filed: December 14, 2016
    Date of Patent: December 3, 2019
    Assignee: Airbus Operations, S.L.
    Inventor: Alexandre Garde La Casa
  • Patent number: 10487752
    Abstract: An overthrust protection system for an aircraft engine. The system comprises an engine overspeed protection unit comprising overspeed logic and an overspeed solenoid valve controlled by the overspeed logic, the overspeed logic configured to energize the overspeed solenoid valve for removing fuel flow to the engine upon detection of an overspeed condition of the aircraft engine; and an overthrust controller coupled to the overspeed protection unit and configured to measure engine thrust and to detect an overthrust condition when an engine thrust threshold has been exceeded, and configured to trigger energizing of the overspeed solenoid valve upon detection of the overthrust condition and an aircraft-on-ground condition.
    Type: Grant
    Filed: March 11, 2015
    Date of Patent: November 26, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Janusz Fiedler, Tatjana Pekovic, Dave Sellors, Amandeep Singh Chahal
  • Patent number: 10480414
    Abstract: A combustor includes fuel nozzles that extend in an axial direction of a combustor main body and are capable of injecting fuel from injection holes on a combustion chamber side. The combustor includes a phase adjusting unit which partially changes a flow path cross-sectional area of at least one of the fuel nozzles in the axial direction such that phases of flow rate fluctuation of fuel do not match with respect to at least two of the fuel nozzles.
    Type: Grant
    Filed: February 14, 2014
    Date of Patent: November 19, 2019
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Mitsunori Isono, Toshihiko Saito, Kotaro Miyauchi
  • Patent number: 10480417
    Abstract: An air turbine starter device comprises a rotor arranged in a cavity of a housing, a first manifold having a cavity with a port operative to direct compressed air to the rotor, a second manifold having a cavity with a port operative to direct compressed air to the rotor, wherein the first manifold is larger than the second manifold.
    Type: Grant
    Filed: July 14, 2016
    Date of Patent: November 19, 2019
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Keith E. Short, Daniel Richard Walker
  • Patent number: 10473029
    Abstract: Apparatus, systems, and methods store energy by liquefying a gas such as air, for example, and then recover the energy by regasifying the liquid and combusting or otherwise reacting the gas with a fuel to drive a heat engine. The process of liquefying the gas may be powered with electric power from the grid, for example, and the heat engine may be used to generate electricity. Hence, in effect these apparatus, systems, and methods may provide for storing electric power from the grid and then subsequently delivering it back to the grid.
    Type: Grant
    Filed: November 18, 2014
    Date of Patent: November 12, 2019
    Inventor: William M. Conlon
  • Patent number: 10465909
    Abstract: The present disclosure is directed to a fuel nozzle for a gas turbine engine. The fuel nozzle includes a sleeve defining a plurality of radially oriented air inlet ports. The sleeve defines a sleeve outlet at the downstream end of the fuel nozzle and a longitudinally extended annular inner wall inward of the sleeve in the radial direction. The inner wall defines a fluid passage and an inner wall outlet, in which the inner wall outlet is disposed toward the downstream end of the inner wall. At least a portion of the plurality of radially oriented air inlet ports is outward of the inner wall along the radial direction. The fuel nozzle further includes a plurality of fuel injectors surrounding the sleeve, in which the sleeve and each of the fuel injectors are connected to an aft body at the downstream end and a forward body at the upstream end.
    Type: Grant
    Filed: November 4, 2016
    Date of Patent: November 5, 2019
    Assignee: General Electric Company
    Inventors: Gregory Allen Boardman, Bassam Sabry Mohammad Abdelnabi