Patents Examined by Scott J Walthour
  • Igniter for gas turbine engine
    Patent number: 11391212
    Abstract: There is provided an igniter for a gas turbine engine including: a base, a glow plug heater rod extending from the base along an axis and terminating in a rod end, the heater rod having a heating section extending axially between axially opposite ends of a heater contained within the heater rod, a heat spreader being in thermal conduction contact with the heating section of the heater rod and extending radially therefrom.
    Type: Grant
    Filed: March 29, 2019
    Date of Patent: July 19, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Michel Bousquet, Richard Freer
  • System and method for providing compressed air to a gas turbine combustor
    Patent number: 11377970
    Abstract: A system for directing cooling air into a gas turbine combustor is provided. The system comprises a transition duct coupled to a flow sleeve, where air to be used for combustor cooling and in the combustion process enters a bellmouth of the transition duct, passes through a plurality of struts within the bellmouth, and is distributed to a passage located between the combustion liner and flow sleeve.
    Type: Grant
    Filed: November 2, 2018
    Date of Patent: July 5, 2022
    Assignee: Chromalloy Gas Turbine LLC
    Inventors: Daniel L. Folkers, Zhenhua Xiao, Vincent C. Martling
  • Decoupler assemblies for engine starter
    Patent number: 11378011
    Abstract: An air turbine starter for starting an engine, comprising a housing defining an inlet, an outlet, and a flow path extending between the inlet and the outlet for communicating a flow of gas there through. A turbine member is journaled within the housing and disposed within the flow path for rotatably extracting mechanical power from the flow of gas. A gear train is drivingly coupled with the turbine member, a drive shaft is operably coupled with the gear train, and an output shaft is selectively operably coupled to rotate with the engine via a decoupler.
    Type: Grant
    Filed: December 18, 2019
    Date of Patent: July 5, 2022
    Assignee: Unison Industries, LLC
    Inventors: Subrata Nayak, Eliel Fresco Rodriguez, David Allan Dranschak, Shiloh Montgomery Emerson Meyers, Pallavi Tripathi
  • Premixed pilot nozzle for gas turbine combustor
    Patent number: 11371706
    Abstract: The premixed pilot nozzle includes axially elongated tubes defined within a plenum between an outer shroud and a first shroud disposed radially inward of the outer shroud. The tubes extend between tube inlets defined through a forward face and tube outlets defined through an aft face. A second shroud is disposed radially inward of the first shroud, thereby defining a fuel plenum between the first shroud and the second shroud, and the fuel plenum is in communication with a gaseous fuel supply. A fuel injection port, which is positioned between the tube inlet and the tube outlet of each tube, is in fluid communication with the fuel plenum. An air supply configured to fluidly communicate with the tube inlet of each tube. The second shroud defines a second plenum therein, the second plenum being coupled to a source of a non-combustible fluid.
    Type: Grant
    Filed: December 18, 2017
    Date of Patent: June 28, 2022
    Assignee: General Electric Company
    Inventors: James Harper, Neal William Grooms, Yon Han Chong, Benjamin Robert Ryan
  • Control device, gas turbine, control method, and program
    Patent number: 11359552
    Abstract: A control device is a control device for a gas turbine including a plurality of combustors and is configured to select combustors to ignite in accordance with a target load on the basis of a predictor which defines a relationship between a load and the number and arrangement of combustors to ignite and a combustion temperature.
    Type: Grant
    Filed: February 11, 2020
    Date of Patent: June 14, 2022
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Keita Yunoki, Kei Inoue, Takashi Hiyama, Eisaku Ito
  • Sleeve assemblies and methods of fabricating same
    Patent number: 11359815
    Abstract: A sleeve assembly for a combustion system includes a first duct including a first circumferential surface and a second duct including a second circumferential surface. The first circumferential surface radially overlaps the second circumferential surface such that the first duct and the second duct collectively define a continuous combustion chamber therein. The continuous combustion chamber is configured to receive high temperature gases flowing therethrough. The sleeve assembly further includes a wear insert removably coupled to the first circumferential surface and extending radially therefrom to engage the second circumferential surface.
    Type: Grant
    Filed: March 10, 2020
    Date of Patent: June 14, 2022
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Kyle Lee Kidder, Zsolt Czirle
  • Systems and methods for operating a turbine engine
    Patent number: 11286855
    Abstract: A turbine system includes a compressor section, an inlet cooling system coupled upstream of the compressor section and configured to cool ambient air entering the compressor section, and a turbine section coupled in flow communication with the compressor section and including at least one hot gas path component. The system further includes a controller configured to receive feedback parameters indicative of a temperature of the at least one hot gas path component, estimate a remaining life of the at least one hot gas path component based on the received feedback parameters, determine a desired power output of the turbine system based on the estimated remaining life of the at least one hot gas path component and a cooling capacity of the inlet cooling system, and control operation of the turbine system to cause the turbine system to generate the desired power output.
    Type: Grant
    Filed: March 15, 2019
    Date of Patent: March 29, 2022
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Ching-Jen Tang, Nilesh Tralshawala
  • Quench aperture body for a turbine engine combustor
    Patent number: 11287132
    Abstract: An assembly for a turbine engine includes a combustor wall. The combustor wall includes a shell, a heat shield and an annular land. The heat shield is attached to the shell. The land extends vertically between the shell and the heat shield. The land extends laterally between a land outer surface and an inner surface, which at least partially defines a quench aperture in the combustor wall. A lateral distance between the land outer surface and the inner surface varies around the quench aperture.
    Type: Grant
    Filed: February 24, 2020
    Date of Patent: March 29, 2022
    Assignee: Raytheon Technologies Corporation
    Inventors: Dennis M. Moura, Jonathan J. Eastwood, Lee E. Bouldin, Monica Pacheco-Tougas
  • Igniter for gas turbine engine
    Patent number: 11286861
    Abstract: There is disclosed an igniter for a gas turbine engine including: a base including a securing assembly configured to be matingly connected to a casing of the gas turbine engine, a glow plug heater rod extending from the base along an axis to a rod end distal from the base, the glow plug heater rod sized such that that the rod end is exposed to a combustion chamber of the gas turbine engine when the base is connected to the casing.
    Type: Grant
    Filed: March 29, 2019
    Date of Patent: March 29, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Richard Freer, Kian McCaldon, Tin-Cheung John Hu, Michel Bousquet, André Fortin
  • Controlling lubricant flow in epicyclic gearbox
    Patent number: 11280221
    Abstract: A disclosed lubrication system for a turbofan engine includes a pump for driving lubricant through a lubrication circuit, at least one sensor generating a signal indicative of an engine operating condition and at least one valve for controlling a flow of lubricant through the lubrication circuit. A controller controls operation of the valve to vary the flow of lubricant based on the engine operating condition to maintain lubricant flow within predefined operating limits.
    Type: Grant
    Filed: October 2, 2019
    Date of Patent: March 22, 2022
    Assignee: Raytheon Technologies Corporation
    Inventors: Paul H. Dolman, Michael E. McCune
  • Burner for a gas turbine and method for operating the burner
    Patent number: 11274609
    Abstract: A burner with a control unit, a combustion chamber, a pressure sensor and fuel stages which are arranged to supply fuel with a respective mass flow to the combustion chamber, wherein the mass flows are controlled by the control unit, wherein the pressure sensor is adapted to measure a pressure sequence in the combustion chamber or in the burner and to transfer the pressure sequence to the control unit which is adapted to perform a Fourier transformation on at least one determined timespan of the pressure sequence to result in a pressure spectrum having a maximum within a frequency band and wherein the control unit is adapted to perform a comparison of the maximum with a predefined threshold and to control the mass flows by using the comparison to reduce and/or to control pressure fluctuations in the combustion chamber.
    Type: Grant
    Filed: February 6, 2019
    Date of Patent: March 15, 2022
    Assignee: Siemens Energy Global GmbH & Co. KG
    Inventors: Philipp Geipel, Annika Lindholm, Rikard Magnusson, Arturo Manrique Carrera
  • Vortex generators for turbine engine exhaust
    Patent number: 11268390
    Abstract: An exhaust system for an engine includes an exhaust nozzle located adjacent an outlet end of the engine to receive a primary flow of exhaust gasses expelled from the engine, an inlet opening formed between the exhaust nozzle and the outlet end of the engine through which a secondary flow is provided to the exhaust nozzle, and a vortex generator arranged within the exhaust system at a position where both the primary flow and the secondary flow are present. The vortex generator interrupts at least one of the primary flow and the secondary flow.
    Type: Grant
    Filed: July 19, 2018
    Date of Patent: March 8, 2022
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: Joseph Lawrence Simonetti, Donald W. Lamb, Jr., Patrick Ormande Bowles
  • Turbine cooling arrangement
    Patent number: 11268444
    Abstract: A cooling system for a component of a gas turbine engine includes a first airflow passage configured to direct a first airflow to a mixing chamber and a second airflow passage to configured direct a second airflow to the mixing chamber, the second airflow having a higher temperature than the first airflow, and a cooling airflow passage to direct a cooling airflow from the mixing chamber to the component, the cooling airflow comprising the first airflow and the second airflow. The airflow passages are configured and sized to allow an amount of cooling airflow for unrestricted engine operation. When the first airflow passage is disabled, the second airflow passage and cooling airflow passage are configured and sized to allow an amount of cooling airflow which is adequate to permit continued safe engine operation restricted to within only a portion of its normal parameters and operating envelope.
    Type: Grant
    Filed: May 18, 2017
    Date of Patent: March 8, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Paul R. Hanrahan, Jonathan Ortiz
  • Combustor heat shield sealing
    Patent number: 11268697
    Abstract: Combustor assemblies for gas turbine engines are provided. For example, a combustor assembly comprises a combustor dome, a first heat shield having an edge, a second heat shield having an edge, and a seal extending from the edge of the first heat shield to the edge of the second heat shield such that the seal spans a gap between the first heat shield and the second heat shield. In another embodiment, the seal has a first contact portion contacting the edge of the first heat shield, a second contact portion contacting the edge of the second heat shield edge, and a connecting portion connecting the first portion and the second portion. The first contact portion and the second contact portion project away from the connecting portion. Methods for sealing between adjacent heat shields of a combustor assembly also are provided.
    Type: Grant
    Filed: August 12, 2019
    Date of Patent: March 8, 2022
    Assignee: General Electric Company
    Inventors: Michael Alan Stieg, Valeria Proano Cadena, Aaron Michael Dziech, Michael Todd Radwanski, Donald Michael Corsmeier
  • Igniter for gas turbine engine
    Patent number: 11268447
    Abstract: There is disclosed an igniter for a gas turbine engine including: a base including a securing assembly configured to be matingly connected to a casing of the gas turbine engine, a glow plug heater rod extending from the base along an axis and terminating in a rod end, a combustor liner plug extending circumferentially around the heater rod, the combustor liner plug being sized and configured to extend inside an aperture in a combustor liner of the gas turbine engine when the base is connected to the casing between the heater rod and a periphery of the aperture.
    Type: Grant
    Filed: March 29, 2019
    Date of Patent: March 8, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Richard Freer, Kian McCaldon, Tin-Cheung John Hu, Michel Bousquet, André Fortin
  • Combustor and gas turbine including the same
    Patent number: 11268698
    Abstract: A combustor includes an inner liner forming a combustion chamber; an outer liner surrounding the inner liner to form a cooling passage in which compressed air flows; and a plurality of cooling guides installed around an inner circumferential surface of the outer liner to surround the combustion chamber, each of the cooling guides protruding from the inner circumferential surface to create an impinging jet from the compressed air flowing in the cooling passage. The plurality of cooling guides surrounding the combustion chamber are installed at regular intervals in a flow direction of the compressed air, and are arranged in staggered axial rows. Each cooling guide includes an air guiding surface facing the flow of the compressed air to guide the compressed air toward the inner liner. Accordingly, liner cooling efficiency can be enhanced by more effectively guiding the impinging jet toward the inner liner.
    Type: Grant
    Filed: October 22, 2018
    Date of Patent: March 8, 2022
    Inventor: Donggon Lee
  • Igniter for gas turbine engine
    Patent number: 11268486
    Abstract: There is disclosed an igniter for a gas turbine engine including: a base, a glow plug heater rod, the glow plug heater rod extending from the base along an axis and terminating in a rod end, a sleeve extending circumferentially around the glow plug heater rod along at least a portion of a length of the glow plug heater rod, the sleeve having an inner surface spaced from the glow plug heater rod to provide a gap between the inner surface and the glow plug heater rod, the gap extending radially relative to said axis.
    Type: Grant
    Filed: March 29, 2019
    Date of Patent: March 8, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Richard Freer, Kian Mccaldon, Tin-Cheung John Hu, Michel Bousquet, André Fortin
  • Slot cooled combustor
    Patent number: 11268696
    Abstract: A combustor for use in a gas turbine engine comprising: an outward shell; an inward shell located radially inward of the outward shell, the inward shell and the outward shell defining a combustion chamber therebetween; an aft outward panel located proximate the outward shell, the aft outward panel extending from an aft end of the combustion chamber to an outward panel joint; an aft inward panel located proximate the inward shell, the aft inward panel extending from the aft end of the combustion chamber to an inward panel joint; and a forward panel located proximate a forward end of the combustion chamber, the forward panel comprising: an outward wall located proximate the outward shell; an inward wall located proximate the inward shell; and a forward wall located proximate the forward end of the combustion chamber, the forward wall extending from the inward wall to the outward wall.
    Type: Grant
    Filed: October 19, 2018
    Date of Patent: March 8, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Gary J. Dillard, Assaf Farah
  • Controller and method
    Patent number: 11261802
    Abstract: A controller for a gas turbine is arranged to supply a load L. The gas turbine includes a fuel supply arranged to supply fuel at a fuel flow rate FF to a combustor, wherein the fuel supply includes a first fuel supply and a second fuel supply. The controller is arranged to determine one or more ratios R of one or more combustor operating parameters COP respectively at the load L to respective reference combustor operating parameters COPR at a reference load LR. The controller is further arranged to control a proportion P of the fuel flow rate FF supplied via the first fuel supply based, at least in part, on the determined one or more ratios R. A gas turbine with the controller and a method controls the gas turbine.
    Type: Grant
    Filed: September 12, 2018
    Date of Patent: March 1, 2022
    Assignee: SIEMENS ENERGY GLOBAL GMBH & CO. KG
    Inventors: Jadeed Beita, Ghenadie Bulat
  • Adaptive bleed schedule in a gas turbine engine
    Patent number: 11261800
    Abstract: An aspect includes a system for a gas turbine engine. The system includes one or more bleeds of the gas turbine engine and a control system configured to check one or more activation conditions of a dirt rejection mode in the gas turbine engine. A bleed control schedule of the gas turbine engine is adjusted to extend a time to hold the one or more bleeds of the gas turbine engine partially open at a power setting above a threshold based on the one or more activation conditions. One or more deactivation conditions of the dirt rejection mode in the gas turbine engine are checked. The dirt rejection mode is deactivated to fully close the one or more bleeds based on the one or more deactivation conditions.
    Type: Grant
    Filed: October 24, 2018
    Date of Patent: March 1, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Christopher J. Hanlon, James F. Krenzer, Becky E. Rose, Mark F. Zelesky