Patents Examined by Ehud Gartenberg
  • Patent number: 11130456
    Abstract: A gas turbine engine and methods of operation include a low pressure electric motor-generator arranged for selective operation in a generator mode to generate electrical power or a drive mode to assist rotation of a low pressure drive shaft of the engine.
    Type: Grant
    Filed: May 9, 2017
    Date of Patent: September 28, 2021
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventors: Donald Klemen, Michael J. Armstrong
  • Patent number: 11131460
    Abstract: A lean burn fuel injector has a head which has a coaxial arrangement of an inner pilot air-blast fuel injector and an outer main air-blast fuel injector. The pilot fuel injector comprises coaxially arranged inner and outer air swirler passages. The main fuel injector comprises coaxially arranged inner and outer air swirler passages. A first splitter is arranged between the passages. The first splitter has a conical divergent downstream portion. A second splitter is arranged radially within and spaced from the first splitter. The second splitter has a conical convergent portion and a conical divergent downstream portion. The downstream end of the second splitter is upstream of the downstream end of the first splitter. A connecting member connects the downstream end of the second splitter and the downstream portion of the first splitter upstream of the downstream end of the first splitter to form a sharp edge.
    Type: Grant
    Filed: February 15, 2019
    Date of Patent: September 28, 2021
    Assignee: Rolls-Royce PLC
    Inventors: Carl L. Muldal, Luca Tentorio, Hua Wei Huang, Juan Carlos Roman Casado
  • Patent number: 11131214
    Abstract: A gas turbine engine includes a gearbox receiving input from a core shaft and driving a fan at a lower speed than the core shaft. First and second oil circuits fluidly couple with an inlet and outlet of the gearbox. A third oil circuit fluidly couples with an inlet and outlet of the gearbox. The outlet of the gearbox includes a device directing oil from the gearbox to the first oil circuit, to the second oil circuit and to the third oil circuit when feeding to the gearbox exceeds a predefined oil flow rate, or deviates an operational value corresponding with that oil flow rate, and directs oil from the gearbox to the third oil circuit when feeding to the gearbox is ? the predefined flow rate or is ? a corresponding operational value or is greater than or equal to a further corresponding operational value.
    Type: Grant
    Filed: April 12, 2019
    Date of Patent: September 28, 2021
    Assignees: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG, ROLLS-ROYCE PLC
    Inventors: Stefan Menczykalski, Stephan Uhkoetter, John R. Mason, David A. Edwards, Neil Davies, Lynn Hammond, David Williams
  • Patent number: 11125114
    Abstract: A turbomachine base plate is disclosed. The base pate includes an upper metal plate and a lower metal plate. The upper metal plate forms a turbomachine supporting surface. The base plate further includes an intermediate layer between the upper metal plate and the lower metal plate and bonded thereto. A frame extends peripherally around the intermediate layer.
    Type: Grant
    Filed: August 23, 2018
    Date of Patent: September 21, 2021
    Assignee: NUOVO PIGNONE TECNOLOGIE SRL
    Inventors: Marco Menchicchi, Paolo Condello, Emanuele Checcacci, Domenico Zaffino
  • Patent number: 11112119
    Abstract: A turbo machine including an annular liner assembly defining a reverse flow combustion chamber is generally provided. The liner assembly includes a first piece defining an inner diameter (ID) combustor inlet portion, an outer diameter (OD) combustor outlet portion, and an outer diameter turbine shroud portion, in which the first piece defines a substantially solid volume between the inner diameter combustor inlet portion and the outer diameter combustor outlet portion.
    Type: Grant
    Filed: October 25, 2018
    Date of Patent: September 7, 2021
    Assignee: General Electric Company
    Inventor: Mackenzie Christopher Hock
  • Patent number: 11105212
    Abstract: Disclosed is a tangential on-board injector (TOBI) system that includes an annulus and a plurality of cooling airflow passages disposed about the annulus. Each cooling airflow passage of the plurality of cooling airflow passages includes an inlet opening having a polygonal inlet cross-section, the inlet opening having an inlet cross-sectional area. Each cooling airflow passage of the plurality of cooling airflow passages further includes an outlet opening having an outlet cross-section and an outlet cross-sectional area. The inlet cross-sectional area is greater in magnitude than the outlet cross-sectional area. Also disclosed are additive manufacturing methods for manufacturing the tangential on-board injector system and gas turbine engines that incorporate the tangential on-board injector system.
    Type: Grant
    Filed: January 29, 2019
    Date of Patent: August 31, 2021
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Michael Ryan Wedig, Jeffrey D Harrison, Mark C Morris, Raymond Gage
  • Patent number: 11085647
    Abstract: A combustor includes a liner having an outlet end to pass combustion gas and a liner flange protruding outward from the outlet end; a transition piece to discharge combustion gas from the liner to a turbine, the transition piece having an inlet end for coupling to the outlet end of the liner and a transition piece flange protruding outward from the inlet end to face the liner flange; and a first elastic support installed on the liner flange to protrude toward the transition piece flange. A force applied from the transition piece elastically deforms an elastic arch of the first elastic support, which includes a movable support that is spaced apart from the liner flange if the force applied from the transition piece does not primarily deform the elastic arch. An auxiliary elastic support installed inside the first elastic support elastically deforms if the force secondarily deforms the elastic arch.
    Type: Grant
    Filed: September 17, 2018
    Date of Patent: August 10, 2021
    Inventor: Heonseop Jin
  • Patent number: 11079113
    Abstract: A fuel injector including a fuel supply tube (8), a plurality of premix tubes (2), a support plate (3) which supports the fuel supply tube and the plurality of premix tubes, a substrate which supports downstream end portions of the plurality of premix tubes, an outer wall which is cylindrical, which forms a plenum (P) inside, a partition plate which partitions the plenum (P) into a fuel plenum (PF) and a cooling air plenum (PA), a baffle which partitions the cooling air plenum (PA) into an upstream cooling air plenum (PA1) and a downstream cooling air plenum (PA2) and has a plurality of cooling holes formed therein, and a cooling air supply tube configured to supply cooling air to the upstream cooling air plenum (PA1), in which the end portion on the downstream side of the fuel supply tube opens in the fuel plenum (PF), and a fuel introduction hole.
    Type: Grant
    Filed: April 27, 2018
    Date of Patent: August 3, 2021
    Assignee: MITSUBISHI POWER, LTD.
    Inventors: Katsuyoshi Tada, Kei Inoue, Satoshi Tanimura, Keijiro Saito
  • Patent number: 11079111
    Abstract: This disclosure provides an air tube for a combustor of a gas turbine engine. The air tube includes an inner tube and an outer tube to deliver discharged compressor air into a combustion chamber of the combustor. The air tube can include struts and fins that can improve the cooling performance of the air tube during operation of the gas turbine engine.
    Type: Grant
    Filed: April 29, 2019
    Date of Patent: August 3, 2021
    Assignee: Solar Turbines Incorporated
    Inventors: German Verduzco, Michael Telfer, Drew Dominique, James Peffley, Taher Basrai, Rasoul Paydar
  • Patent number: 11060729
    Abstract: A fuel nozzle assembly and a gas turbine combustor including the same are provided. The fuel nozzle assembly may include an end plate coupled to one end of an annular casing, and a fuel nozzle configured such that one end thereof is supported by the end plate and the other end thereof extends outward. The fuel nozzle may include a center fuel nozzle and a plurality of side fuel nozzles arranged annularly to surround the center fuel nozzle. The side fuel nozzle may include a nozzle body located at a center thereof, a shroud spaced outward from the nozzle body, and a plurality of swirlers located between the nozzle body and the shroud. Each of the swirlers may include a leading edge directed toward the end plate and a trailing edge located opposite the leading edge. In each of the side fuel nozzles, distances between the leading edges are different from each other.
    Type: Grant
    Filed: July 16, 2020
    Date of Patent: July 13, 2021
    Inventors: U Jin Roh, Mu Hwan Chon
  • Patent number: 11047303
    Abstract: A supply duct of a compressor of a turbine engine, formed from internal and external walls of revolution around an axis and opposite one another to define a circulation stream of a fluid, is provided. The stream allows the fluid to be routed from the inlet of the duct to the inlet of the compressor. The radius of the external wall at the inlet of the duct is greater than the radius of the duct at the inlet of the compressor. The duct includes a portion for which the radius of the external wall along the portion is less than the radius of the external wall at the inlet of the compressor, and the radius of the internal wall along the portion of the duct is less than the radius of the internal wall at the inlet of the compressor.
    Type: Grant
    Filed: July 23, 2018
    Date of Patent: June 29, 2021
    Assignee: Safran Aircraft Engines
    Inventors: Jacky Novi Mardjono, Norman Bruno André Jodet
  • Patent number: 11047337
    Abstract: A gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan rotor. Aspects of the gear system are provided with defined flexibility. The fan drive turbine has a first exit area and rotates at a first speed. A second turbine section has a second exit area and rotates at a second speed, which is faster than said first speed. A performance quantity can be defined for both turbine sections as the products of the respective areas and respective speeds squared. A performance quantity ratio of the performance quantity for the fan drive turbine to the performance quantity for the second turbine section is between 0.5 and 1.5.
    Type: Grant
    Filed: April 12, 2017
    Date of Patent: June 29, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Michael E. McCune, Jason Husband, Frederick M. Schwarz, Daniel Bernard Kupratis, Gabriel L. Suciu, William K. Ackermann
  • Patent number: 11046445
    Abstract: A nacelle may comprise an inlet cowling comprising an inlet cowling aft edge having an aft edge length; a boat tail cowling comprising a boat tail cowling forward edge having a forward edge length, wherein the boat tail cowling forward edge is disposed adjacent to the inlet cowling aft edge. The forward edge length may be shorter than the aft edge length, forming a step being defined by a portion of the inlet cowling aft edge that is radially outward of the boat tail cowling forward edge. The nacelle may further comprise a transition fairing coupled to the boat tail cowling, wherein the transition fairing comprises a fairing forward edge disposed adjacent to the inlet cowling aft edge and a fairing ramp surface spanning between the inlet cowling aft edge and a boat tail cowling external surface.
    Type: Grant
    Filed: July 26, 2017
    Date of Patent: June 29, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Dmitriy B. Sidelkovskiy, Steven H. Zysman
  • Patent number: 11041443
    Abstract: A multi-spool gas turbine engine comprises a low pressure (LP) spool and a high pressure (HP) spool independently rotatable about a central axis extending through an accessory gear box (AGB). The LP spool has an LP compressor, which is axially positioned between the HP compressor of the HP spool and the AGB. A tower shaft drivingly connects the HP spool to the AGB.
    Type: Grant
    Filed: September 26, 2019
    Date of Patent: June 22, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Eric Durocher, Keith Morgan, Lazar Mitrovic, Jean Dubreuil, Martin Poulin
  • Patent number: 11015529
    Abstract: A combustion liner or component produced through the use of additive manufacturing techniques. The combustion liner or other component may be formed having a feature based optimized cooling circuit at least partially embedded in the thickness of the material. The internal cooling circuit, may be used, along with other benefits, to control the temperature of the component and prevent hot-spots and uneven heat distribution across the surface of the component.
    Type: Grant
    Filed: December 23, 2016
    Date of Patent: May 25, 2021
    Assignee: General Electric Company
    Inventor: Aaron Wertz
  • Patent number: 11015613
    Abstract: A shroud assembly includes a shroud segment and a hanger. In one exemplary aspect, the shroud segment has a shroud body extending substantially along a circumferential direction between a first end and a second end. The shroud body defines a radial centerline along the circumferential direction. A flange is attached to or integral with the shroud body. The flange is pivotally coupled with the hanger at a location spaced from the radial centerline of the shroud body.
    Type: Grant
    Filed: January 12, 2017
    Date of Patent: May 25, 2021
    Assignee: General Electric Company
    Inventors: Daniel Patrick Kerns, Dennis Paul Dry, Megan Elizabeth Scheitlin, Alexander Martin Sener, Jason David Shapiro
  • Patent number: 11008116
    Abstract: A gas turbine engine includes a supply air conduit fluidly connected to an inlet of a combustion chamber to convey supply air to the combustion chamber, an exhaust conduit fluidly connected to an exit of the combustion chamber to convey exhaust gases away from the combustion chamber, and a recuperator defining a first flow path and a second flow path therethrough, the second flow path being in heat transfer communication with the first flow path, the first flow path defining part of the supply air conduit, the second flow path defining part of the exhaust conduit. Methods of operating the engine are also provided.
    Type: Grant
    Filed: April 15, 2019
    Date of Patent: May 18, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Andreas Eleftheriou, Daniel Alecu, Enzo Macchia
  • Patent number: 11007955
    Abstract: A gas turbine engine and methods of operation include a low pressure electric motor-generator having an electrical assembly for electrical connection.
    Type: Grant
    Filed: May 9, 2017
    Date of Patent: May 18, 2021
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventors: Donald Klemen, Michael J. Armstrong
  • Patent number: 10987733
    Abstract: A component formed by an additive manufacturing process includes a body and a first vibration damper. The body is formed from an additive manufacturing material, and defines at least a first cavity completely enclosed within the body. The first vibration damper is disposed within the first cavity. The first vibration damper includes a flowable medium and a first solidified element formed from the additive manufacturing material. The flowable medium surrounds the first solidified element.
    Type: Grant
    Filed: February 22, 2018
    Date of Patent: April 27, 2021
    Assignee: General Electric Company
    Inventors: Daniel Jason Erno, Robert Arvin Hedeen, Prabhjot Singh
  • Patent number: 10982595
    Abstract: A gas turbine engine has a compressor section including a lower pressure compressor and a higher pressure compressor, and a turbine section. A core engine housing surrounds the compressor section and the turbine section. An outer intermediate housing wall defines an internal chamber between the core housing and the outer intermediate housing. A fan rotor and a fan casing surround the fan rotor to define a bypass duct between the fan case and the outer intermediate housing. A heat exchanger is mounted in the internal chamber and receives high pressure air for cooling the high pressure air and delivering the high pressure air into the core engine housing to be utilized as cooling air for a component. Air from the lower pressure compressor is utilized to cool the higher pressure air in the heat exchanger.
    Type: Grant
    Filed: August 23, 2016
    Date of Patent: April 20, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Frederick M. Schwarz, Paul W. Duesler