Patents Examined by Jason H Duger
  • Combined cycle power system with an auxiliary steam header supplied by a flasher and a surplus steam leak
    Patent number: 10876432
    Abstract: A combined cycle power system includes a gas turbine exhausting an exhaust gas, a heat recovery steam generator including, a first economizer, a first steam generator, a second economizer, a second steam generator, a steam turbine which is driven by the steam generated at the first steam generator and the second steam generator, and a flasher which generates a first flash steam and a first drain water by flashing a portion of the water heated by the first economizer.
    Type: Grant
    Filed: September 5, 2018
    Date of Patent: December 29, 2020
    Assignee: KABUSHIKI KAISHA TOSHIBA
    Inventors: Takahisa Hoshino, Masashi Kimura
  • Inlet cowl for a turbine engine
    Patent number: 10837362
    Abstract: The disclosure is towards an inlet cowl for a turbine engine including a surface defining an inlet with a flow path and a method towards controlling the airflow in the flow path. The inlet cowl further includes an inlet lip and inner and outer barrels. The inlet lip confronts the inner barrel at a junction defining a gap.
    Type: Grant
    Filed: October 12, 2016
    Date of Patent: November 17, 2020
    Assignee: General Electric Company
    Inventors: Mustafa Dindar, Joseph Donofrio, Richard David Cedar, David William Crall
  • Combustion chamber shingle arrangement of a gas turbine
    Patent number: 10837646
    Abstract: A combustion chamber shingle arrangement of a gas turbine, including a combustion chamber shingle, at least one threaded bolt configured for attaching the combustion chamber shingle, and a base body connecting the threaded bolt to the combustion chamber shingle, wherein the base body comprises a platform and a connection area that connects the platform to the combustion chamber shingle, wherein the threaded bolt is arranged at the platform, and wherein a hollow space is embodied between the platform and the combustion chamber shingle.
    Type: Grant
    Filed: February 26, 2018
    Date of Patent: November 17, 2020
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Carsten Clemen, Michael Ebel, Kay Heinze, Stefan Penz
  • Transverse-mounted power turbine drive system
    Patent number: 10830129
    Abstract: The present disclosure relates generally to an aircraft with counter-rotating pusher props powered by a gas turbine engine having a power turbine disposed substantially perpendicular to the compressor, combustor and turbine gas generator power core axis, as well as to the aircraft longitudinal axis.
    Type: Grant
    Filed: December 12, 2014
    Date of Patent: November 10, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Wesley K. Lord
  • Combustor liner panel end rail with curved interface passage for a gas turbine engine combustor
    Patent number: 10830434
    Abstract: A combustor for a gas turbine engine includes a support shell; a first liner panel mounted to the support shell via a multiple of studs, the first liner panel including a first rail that extends from a cold side of the first liner panel such that the rail is non-perpendicular to the cold side and includes a concave surface to at least partially form a curved interface passage; and a second liner panel mounted to the support shell via a multiple of studs, the first liner panel including a second rail that extends from a cold side of the second liner panel and includes a convex surface to at least partially form the curved interface passage.
    Type: Grant
    Filed: February 23, 2017
    Date of Patent: November 10, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: San Quach, Jeffrey T. Morton, Matthew D. Parekh
  • Diffusing hole for rail effusion
    Patent number: 10830435
    Abstract: A heat shield panel for use in a gas turbine engine combustor is disclosed. The heat shield panel includes a hot side defining a first surface having an outer perimeter, a cold side defining a second surface spaced from the first surface, a rail member disposed on the cold side proximate a first portion of the outer perimeter, the rail member having an outer wall and an inner wall, and an orifice extending through the rail member, from the inner wall to the outer wall, the orifice having a cross sectional area that increases from the inner wall to the outer wall.
    Type: Grant
    Filed: February 6, 2018
    Date of Patent: November 10, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Jon E Sobanski, Steven D Porter
  • Gas turbine engine structural guide vanes
    Patent number: 10822970
    Abstract: A structural guide vane may include a first root, a second root positioned radially outward from the first root and a truss extending between the first root and second root. The truss may be made of a first material. The guide vane may further include an overmold made of a second material that surrounds the truss to form an airfoil.
    Type: Grant
    Filed: October 21, 2015
    Date of Patent: November 3, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: William Richard Ganoe, Thomas B. Hyatt
  • Method and system for limiting power of an engine
    Patent number: 10823113
    Abstract: Systems and methods for limiting power of a gas turbine engine for an aircraft are described herein. A blade angle of a propeller blade of the engine and a commanded power for the engine are obtained. A thrust transition direction is determined. The commanded power is compared to a selected threshold based on the blade angle and the thrust transition direction. Power to the engine is limited when the commanded power exceeds the selected threshold.
    Type: Grant
    Filed: August 21, 2017
    Date of Patent: November 3, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Sylvain Lamarre, Simon Lopez, Nicolas Des Roches-Dionne, Michael Conciatori
  • System and method for reducing specific fuel consumption (SFC) in a turbine powered aircraft
    Patent number: 10808611
    Abstract: A system for providing auxiliary power in an aircraft. A propulsion core comprises a compressor, a combustor, a turbine, and a shaft. An accessory unit comprises an accessory combustor, an accessory turbine, and an accessory shaft. A tank is configured to hold high pressure air and operably connected to the accessory unit. An electric generator comprises an electrical output and a mechanical input, with the mechanical input operably connected to the accessory shaft and the electrical output operably connected to an electric motor operably connected to the shaft. The electrical output is operably connected to an auxiliary power consuming device in the aircraft.
    Type: Grant
    Filed: August 26, 2019
    Date of Patent: October 20, 2020
    Assignee: Rolls-Royce Corporation
    Inventor: Michael Abraham Karam
  • Impingement cooling baffle
    Patent number: 10781715
    Abstract: A component for a gas turbine engine includes a first component end, a second component end and a cavity extending from the first component end to the second component end. A baffle assembly is located in the cavity including a first baffle portion inserted into the cavity and a second baffle portion inserted into the cavity. The first baffle portion overlaps the second baffle portion. A vane for a gas turbine engine includes an outer platform, an inner platform and an airfoil portion extending. A core extends through the airfoil portion. A baffle is positioned in the core and is offset from the core wall. The baffle includes a first baffle portion inserted into the core and a second baffle portion inserted into the core. One of the first baffle portion or the second baffle portion overlaps the other of the first baffle portion or the second baffle portion.
    Type: Grant
    Filed: December 21, 2015
    Date of Patent: September 22, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Tracy A. Propheter-Hinckley
  • Compressor with stator vane configuration in vicinity of bleed structure, and gas turbine engine
    Patent number: 10774750
    Abstract: A compressor includes: a plurality of vanes at a vane stage provided to a rotor casing demarcating the primary duct; an air bleed chamber casing that demarcates an air bleed chamber interconnecting with the primary duct; and an air bleed tubing connected to the air bleed chamber casing. Of the plurality of vanes, when a plurality of vanes positioned at a region including the position in the peripheral direction corresponding to the air bleed tubing are a first vane group and a plurality of vanes other than the first vane group are a second vane group, the spacing between the ends at the outside in the radial direction of the vanes that are adjacent in the first vane group is closer than the spacing between the ends at the outside in the radial direction of the vanes that are adjacent in the second vane group.
    Type: Grant
    Filed: February 7, 2014
    Date of Patent: September 15, 2020
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventor: Thomas Walker
  • Combustor tile with monolithic inserts
    Patent number: 10767863
    Abstract: An annular assembly for a gas turbine engine and a method of making the annular assembly. The annular assembly comprises a supporting member comprising metal and including a support hole therethrough, and a liner tile made of ceramic matrix composite material. A plurality of the liner tile form an annular liner to shield hot combustion gases produced by the gas turbine engine. The liner tile is disposed adjacent the supporting member. A connecting member comprising ceramic material has a base element and a stem. The base element is embedded in the liner tile during construction of the liner tile to form an integrated structure therewith. A distal end of the stem passes through the support hole and is mated with a retaining member to retain the liner tile adjacent the supporting member.
    Type: Grant
    Filed: July 22, 2016
    Date of Patent: September 8, 2020
    Assignees: Rolls-Royce North American Technologies, Inc., Rolls-Royce Corporation
    Inventors: Ted Joseph Freeman, Bruce E. Varney, Andrew Joseph Lazur
  • Method for controlling the operation of a gas turbine with an averaged turbine outlet temperature
    Patent number: 10767569
    Abstract: A method is disclosed for operating a gas turbine having a compressor, a combustor, a turbine downstream of the combustor, and a total number of turbine outlet temperature measurements. The method includes locally measuring the turbine outlet temperature of the turbine with the turbine outlet temperature measurements of the respective turbine, and averaging measured temperatures of the selected turbine outlet temperature measurements to obtain an average turbine outlet temperature. The gas turbine operation is controlled depending on the determined average turbine outlet temperature.
    Type: Grant
    Filed: November 14, 2016
    Date of Patent: September 8, 2020
    Assignee: Ansaldo Energia Switzerland AG
    Inventors: Martin Gassner, Andreas Jan Schesny, Sebastian Lipari, Stefano Bernero, Manuel Ramirez-Espana-Mejia, Mengbin Zhang
  • Method for controlling a lifting jack for an aircraft engine nacelle, a jack-type lifting system implementing the method and the thus equipped nacelle
    Patent number: 10767672
    Abstract: The jack-type lifting system includes a valve for modifying a maximum force value of a lifting jack activated by a protrusion for determining a determined portion such as the beginning of the extension stroke of the lifting jack. Thanks to the modification of the maximum force value, a pressure source thus applies the full force of the lifting jack after a start-up stroke so as to protect a lock of a reverser cowl which has been forgotten during maintenance.
    Type: Grant
    Filed: December 28, 2015
    Date of Patent: September 8, 2020
    Assignee: Safran Nacelles
    Inventors: Vincent Le Coq, Marc Gerome
  • Jet in cross flow fuel nozzle for a gas turbine engine
    Patent number: 10760793
    Abstract: The present disclosure is directed to a fuel nozzle assembly for a gas turbine engine. The fuel nozzle assembly includes a centerbody extended along a nozzle centerline axis and generally concentric thereto and an outer sleeve surrounding the centerbody and extended along the nozzle centerline axis and generally concentric thereto. The centerbody defines an outer wall extended at least partially along the nozzle centerline axis in which the centerbody defines a first fuel passage therewithin and one or more first fuel exit openings through the outer wall. Each first fuel exit opening is discrete from another along the outer wall. The outer sleeve and centerbody together define a first air passage therebetween. The first fuel passage and the first fuel exit opening are in fluid communication with the first air passage.
    Type: Grant
    Filed: July 21, 2017
    Date of Patent: September 1, 2020
    Assignee: General Electric Company
    Inventors: Nayan Vinodbhai Patel, Alfred Albert Mancini, Duane Douglas Thomsen, Michael Anthony Benjamin
  • Turbomachine designed to operate in turning gear mode
    Patent number: 10753280
    Abstract: A field of turbine engines, and more particularly to an engine including a compressor; a combustion chamber; a first turbine connected to the compressor by a first rotary shaft; an actuator device for actuating the first rotary shaft in order to keep the first turbine and the compressor in rotation while the combustion chamber is extinguished; and a lubrication circuit for lubricating the engine. The circuit passes through at least one heat source suitable for heating the lubricant in the lubrication circuit while the first turbine and the compressor are rotating with the combustion chamber extinguished.
    Type: Grant
    Filed: September 29, 2014
    Date of Patent: August 25, 2020
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Romain Thiriet, Vincent Poumarede, Camel Serghine
  • Gas turbine facility exhaust gas supply heat exchange arrangement
    Patent number: 10738657
    Abstract: A gas turbine facility of an embodiment includes: a combustor casing; a combustor provided in the combustor casing; a cylinder surrounding a periphery of the combustor and dividing a space between the combustor casing and the combustor; a turbine rotated by combustion gas exhausted from the combustor; a heat exchanger cooling the combustion gas exhausted from the turbine; a pipe through which a part of the combustion gas cooled in the heat exchanger passes in the heat exchanger to be heated, the pipe guiding the combustion gas heated in the heat exchanger into the cylinder; and a pipe guiding another part of the combustion gas cooled in the heat exchanger to a space between the combustor casing and the cylinder.
    Type: Grant
    Filed: August 16, 2017
    Date of Patent: August 11, 2020
    Assignee: Toshiba Energy Systems & Solutions Corporation
    Inventors: Yuichi Morisawa, Hideyuki Maeda, Yasuaki Nakamura, Yasunori Iwai, Masao Itoh
  • Air shrouds with air wipes
    Patent number: 10731860
    Abstract: An air shroud for a nozzle includes an air shroud body defining an inlet and an outlet in fluid communication with one another to allow an outer airflow to issue therefrom. The air shroud also includes an air wipe disposed outboard of the air shroud body including a web defining a plurality of air wipe outlets in fluid communication with a downstream surface of the air shroud body such that air can flow through the air wipe outlets and wipe the downstream surface of the air shroud body. The air wipe can be integral with the air shroud body.
    Type: Grant
    Filed: February 5, 2015
    Date of Patent: August 4, 2020
    Assignee: DELAVAN, INC.
    Inventors: Matthew R. Donovan, David H. Bretz, Philip E. Buelow
  • Apparatus and method for sealing turbine assembly
    Patent number: 10704405
    Abstract: A turbine or turbine system includes a compressor, a combustor, a turbine section, a diffuser with a parting line between two components, and a seal along the parting line. The seal includes a protrusion, a recess, and a flexible portion between the protrusion and the recess. The flexible portion has a bent cross-section perpendicular to the parting line. An outer surface of the bent cross-section contacts an inner surface of the recess. An inner surface of the bent cross-section contacts an outer surface of the protrusion. Sealing a parting line between two parts of a diffuser in a gas turbine system includes disposing a flexible portion between a protrusion and a recess of the two parts, contacting an outer surface of the bent cross-section with an inner surface of the recess, contacting an inner surface of the bent cross-section with an outer surface of the protrusion, and pressurizing the diffuser.
    Type: Grant
    Filed: April 2, 2014
    Date of Patent: July 7, 2020
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Srinivas Pakkala, Robert Jamiolkowski, Tomasz Jendrzejewski, Rohit Pruthi
  • Premixing fuel injectors and methods of use in gas turbine combustor
    Patent number: 10690349
    Abstract: A fuel injector for a gas turbine combustor includes side wall fuel injection bodies extending between opposite end walls. Each side wall fuel injection body defines a fuel plenum and includes an outer surface defining fuel injection ports in communication with the fuel plenum. One or more fuel injection bodies extending between the end walls are positioned between the side wall fuel injection bodies. Each fuel injection body defines a fuel plenum and includes an outer surface defining fuel injection ports in fluid communication with the fuel plenum. A conduit fitting coupled to the frame is fluidly connected to the respective fuel plenums. The fuel injection ports fluidly communicate with air flow paths defined between the fuel injection bodies and the side wall fuel injection bodies. A combustor for a gas turbine includes a liner and an axial fuel staging system with the present fuel injector.
    Type: Grant
    Filed: September 1, 2017
    Date of Patent: June 23, 2020
    Assignee: General Electric Company
    Inventors: Jayaprakash Natarajan, Seth Reynolds Hoffman, Ronnie Ray Pentecost, Wei Zhao