Patents Examined by Alain Chau
  • Intercooled cooling air using cooling compressor as starter
    Patent number: 10830149
    Abstract: A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream discharge, and more upstream locations. A turbine section has a high pressure turbine. A tap taps air from at least one of the more upstream locations in the compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger, and delivers air into the high pressure turbine. The cooling compressor is connected to be driven with at least one rotor in the main compressor section. A source of pressurized air is selectively sent to the cooling compressor to drive a rotor of the cooling compressor to rotate, and to in turn drive the at least one rotor of the main compressor section at start-up of the gas turbine engine. An intercooling system is also disclosed.
    Type: Grant
    Filed: August 9, 2018
    Date of Patent: November 10, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Nathan Snape, Gabriel L. Suciu, Brian D. Merry
  • Fuel supply pipeline system for gas turbine
    Patent number: 10830156
    Abstract: A fuel supply line system used for a gas turbine, including: fuel gas control valves used for controlling delivery to the gas turbine; a first line used for connecting the fuel gas source to the control valves; a second line used for connecting the control valves to the gas turbine; a monitoring device, configured to be used for determining the pressure inside the pipe at the outlet of the second line near said control valve; and a controller, configured to reduce the effective flow area of the pressure control valves or close the control valves when the determined pressure inside the pipe of the second line is greater than a predetermined pressure.
    Type: Grant
    Filed: February 19, 2014
    Date of Patent: November 10, 2020
    Assignee: SIEMENS AKTIENGESELLSCHAFT
    Inventors: Mariano Cano Wolff, Du-Fhan Choi, Kai Hausmann, Song Jun Lv, Peter-Andreas Schneider, Julius Schwager
  • Compressor diffuser with diffuser pipes varying in natural vibration frequencies
    Patent number: 10823196
    Abstract: The diffuser pipe assembly for a compressor of a gas turbine engine includes diffuser pipes circumferentially distributed around a central axis and configured for distributing a flow of compressed air from the compressor to the combustor. Each of the diffuser pipes curving between an inlet end and an outlet end. A first subset of the diffuser pipes has a natural vibration frequency different than a natural vibration frequency of at least a second subset of the diffuser pipes. A method of operating a compressor including the diffuser pipe assembly is also disclosed.
    Type: Grant
    Filed: August 10, 2018
    Date of Patent: November 3, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Ignatius Theratil, Krishna Prasad Balike, Aldo Abate
  • Turbine engine for reducing rotor bow and method thereof
    Patent number: 10823014
    Abstract: The present disclosure provides a turbine engine, comprising a core turbine engine comprising a turbine and a compressor adapted to be driven by the turbine via a rotor; as accessory gearbox connected with the rotor; and a flexible shaft having a first end connected with the accessory gearbox and a second end extending toward outside for being coupled to an external power source.
    Type: Grant
    Filed: December 13, 2017
    Date of Patent: November 3, 2020
    Assignee: General Electric Company
    Inventor: Tod Robert Steen
  • Sweeping jet swirl nozzle
    Patent number: 10823062
    Abstract: An injector head for an anti-icing system may comprise a body having a first surface, a second surface, a face, and an inlet, a first sweeping jet nozzle having a first exit port through the face, wherein the first sweeping jet nozzle comprises a fluid oscillator defining a first sweeping plane of the first sweeping jet nozzle, and a distribution manifold within the body in fluid communication with the inlet and the first sweeping jet nozzle.
    Type: Grant
    Filed: July 27, 2018
    Date of Patent: November 3, 2020
    Assignee: ROHR, INC.
    Inventor: Radhakrishna Chilukuri
  • Igniter with protective alumina coating for turbine engines
    Patent number: 10815896
    Abstract: A high temperature article, for example an igniter for a combustor is presented. The igniter includes a central electrode having a discharge end, an insulator sleeve surrounding the central electrode and a tubular electrode shell surrounding the insulator sleeve. The tubular electrode shell has a forward end projecting beyond the discharge end. The tubular electrode shell includes an iron-based alloy. The igniter further includes a protective coating including alumina disposed on a surface of the forward end. A combustor of a turbine engine, including the igniter is also presented.
    Type: Grant
    Filed: December 5, 2017
    Date of Patent: October 27, 2020
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Daniel Qi Tan, Shekhar Shripad Kamat, Wei Zhang, Javier Guzman Padilla, Santiago Blackaller Ledesma
  • Gas turbine engine de-icing system
    Patent number: 10815884
    Abstract: A de-icing system for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a forward assembly and a rear assembly adjacent to the forward assembly. One of the forward assembly and the rear assembly is rotatable relative to the other to generate an amount of air friction between said forward and rear assemblies. A method of de-icing a gas turbine engine is also disclosed.
    Type: Grant
    Filed: July 26, 2018
    Date of Patent: October 27, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Thomas W. Ward, Scot A. Webb
  • Heat flux measurement system
    Patent number: 10815817
    Abstract: A turbine section according to an example of the present disclosure includes, among other things, a component including a coating on a substrate, and at least one sensor positioned a distance from the component, the at least one sensor configured to detect radiation emitted from at least one localized region of the coating at a first wavelength and configured to detect radiation emitted from the substrate corresponding to the at least one localized region at a second, different wavelength. The first wavelength and the second wavelength are utilized to determine a heat flux relating to the at least one localized region. A method of measuring a gas turbine engine component is also disclosed.
    Type: Grant
    Filed: January 21, 2016
    Date of Patent: October 27, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Shayan Ahmadian, Charles W. Haldeman, Mark F. Zelesky, Christopher T. Bergman, Sebastian Martinez
  • Systems and methods for turbine engine particle separation
    Patent number: 10816014
    Abstract: A turbine engine incorporating a fine particle separation means. The turbine engine includes: a compressor, a diffuser, and a flow path positioned downstream from the diffuser, wherein the flow path comprises an outer annular wall and an inner annular wall between which the compressed air flows, and wherein the flow path comprises an arc that redirects the compressed air from flowing in a substantially radial flow direction to a substantially axial flow direction. The turbine engine further includes an extraction slot in the outer annular wall that fluidly connects with a scavenge plenum, the extraction slot also being positioned downstream axially along the flow path from the arc. The turbine engine further includes an aspiration slot, downstream from the extraction slot, that allows air from the plenum to recirculate back into the flow path.
    Type: Grant
    Filed: July 25, 2018
    Date of Patent: October 27, 2020
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Shakeel Nasir, John Schugardt, Mahmoud Mansour, Richard Bonvouloir
  • Thimble assemblies for introducing a cross-flow into a secondary combustion zone
    Patent number: 10816203
    Abstract: A thimble assembly, which directs fluid flow through a combustor liner, includes a thimble boss and a thimble. The thimble boss is mounted an outer surface of the liner and surrounds a liner opening, thus defining a thimble boss passage. The thimble is disposed through the passage and the liner opening. The thimble wall extends from an inlet portion to an outlet of the thimble. The inlet portion has a greater diameter than the outlet and defines an inlet plane and a parallel intermediate plane. A terminal plane, parallel to the intermediate plane, includes an array of points most distant from a corresponding array of points defining the intermediate plane. The thimble wall has a non-uniform length, such that the outlet of the thimble is oriented at an oblique angle relative to the terminal plane. The thimble wall may have an arcuate shape defined as one-fourth of an ellipse.
    Type: Grant
    Filed: December 11, 2017
    Date of Patent: October 27, 2020
    Assignee: General Electric Company
    Inventors: Charlie Edmond Jones, James Harper, Matthew Bernard Wilson, Robert Wade Clifford, Yon Han Chong, Gilbert Otto Kraemer
  • Combustor assembly with primary and auxiliary injector fuel control
    Patent number: 10815893
    Abstract: A gas turbine combustor assembly includes: a primary combustion chamber in fluid communication with a primary fuel outlet of a primary fuel injector; a torch igniter coupled to the primary combustion chamber, the torch igniter including an auxiliary combustion chamber and an auxiliary fuel injector having an auxiliary fuel outlet in fluid communication with the auxiliary combustion chamber; and a fuel circuit including a first supply flowpath between a fuel inlet and the primary fuel injector, a second supply flowpath between the fuel inlet and the auxiliary fuel injector, and a bypass flowpath between the auxiliary fuel injector and the primary fuel injector.
    Type: Grant
    Filed: January 4, 2018
    Date of Patent: October 27, 2020
    Assignee: Woodward, Inc.
    Inventors: Joel W. Kleckler, Bidhan Dam
  • Plant control apparatus, plant control method and power plant
    Patent number: 10808567
    Abstract: In one embodiment, a plant control apparatus controls a power plant that includes a combustor to burn fuel with oxygen introduced from an inlet guide vane to generate gas, a gas turbine driven by the gas from the combustor, a heat recovery steam generator to generate steam using heat of an exhaust gas from the gas turbine, and a steam turbine driven by the steam from the heat recovery steam generator. The apparatus controls an angle of the inlet guide vane before a start of the steam turbine to a first angle, controls the angle of the inlet guide vane after the start of the steam turbine to a second angle larger than the first angle, and reduce the angle of the inlet guide vane from the second angle to the first angle or more during the predetermined period.
    Type: Grant
    Filed: July 18, 2018
    Date of Patent: October 20, 2020
    Assignees: KABUSHIKI KAISHA TOSHIBA, TOSHIBA ENERGY SYSTEMS & SOLUTIONS CORPORATION
    Inventors: Mizu Kajihara, Masayuki Tobou, Takahiro Mori
  • Stack energy control in combined cycle power plant using heating surface bypasses
    Patent number: 10808578
    Abstract: A combined cycle power plant and method for operating a combined power plant with stack energy control are presented. The combined cycle power plant includes a gas turbine, a heat recovery steam generator including a plurality of heating surfaces, and a steam turbine. The heating surfaces may be partially bypassed to reduce steam production in the heat recovery steam generator during power plant startup. Less energy may be extracted from exhaust gas of the gas turbine. More energy may be dumped through an exhaust stack. The steam turbine may start without restriction of a gas turbine load during power plant startup. The steam turbine may start without increasing a size of an air cooled condenser while maintaining a higher load of a gas turbine during power plant startup.
    Type: Grant
    Filed: December 22, 2015
    Date of Patent: October 20, 2020
    Assignee: SIEMENS AKTIENGESELLSCHAFT
    Inventors: Uygar O. Selman, Matthew Kalish, Stephanie Boisvert, Ankur Deshmukh, Marc Fimpel, Balaji Ramamurthy, Miguel Cancelado, Peter Witte, Peter Simon Rop
  • Gas turbine engine including a rectifierless electronic control unit and method for supplying power to same
    Patent number: 10801414
    Abstract: A gas turbine engine comprises an electronic control unit adapted to control functions of the gas turbine engine and having a DC power input unit coupled to receive DC supply power and an ignition igniter coupled thereto. The ignition exciter includes an AC power input unit adapted to receive AC power from an AC power source within the gas turbine engine, a power rectification unit coupled to receive the AC power from the AC power source and configured, upon receipt thereof, to rectify the AC power into DC power, and a DC power output unit coupled to receive the DC power from the power rectification unit and configured to supply the DC power to the DC power input unit of the electronic control unit as DC supply power and/or the ignition igniter.
    Type: Grant
    Filed: January 24, 2017
    Date of Patent: October 13, 2020
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventor: Jeff M. Kelly
  • Method for operating a gas turbine installation and a gas turbine installation for carrying out the method
    Patent number: 10794297
    Abstract: A method for operating a gas turbine installation with a measured compressor inlet temperature (Ti-actual) and a virtually constant turbine inlet temperature (TiTiso), wherein to provide safe operation of the gas turbine installation, an increase in a calculated exhaust gas temperature (ATK) is compensated by a reduced mass flow (m) of a flow medium flowing through a compressor of the gas turbine installation. An arrangement for operating the gas turbine installation includes a functional unit and a gas turbine installation with a compressor, a turbine, a control system for operating the method.
    Type: Grant
    Filed: January 21, 2015
    Date of Patent: October 6, 2020
    Assignee: Siemens Aktiengsellschaft
    Inventors: Daniel Burkhardt, Matthias Stieger
  • Gas turbine combustor and method of operating the same
    Patent number: 10794296
    Abstract: The gas turbine combustor and the operation method thereof are designed to minimize visualization of exhaust gas from the gas turbine upon switching of the gas turbine fuel from the oil fuel to the gas fuel. Upon switching of the combustion by the pilot burner from the oil burning to the gas burning, the gas fuel is supplied to the main burners so as to start the gas burning. Then the gas fuel is supplied to the pilot burner to start the gas burning.
    Type: Grant
    Filed: October 23, 2017
    Date of Patent: October 6, 2020
    Assignee: Mitsubishi Hitachi Power Systems, Ltd.
    Inventors: Yasuhiro Akiyama, Mitsuhiro Karishuku, Keita Naito, Kanetsugu Nakamura, Satoshi Dodo, Tomohiro Asai, Yoshitaka Hirata, Akinori Hayashi
  • Gas turbine engine having instrumented airflow path components
    Patent number: 10794281
    Abstract: Instrumented airflow path components configured to determine airflow path distortion in an airflow path of a gas turbine engine (e.g., using for propulsion of an aircraft) are provided. In one embodiment, a gas turbine engine for an aircraft can include a compressor section, a combustion section, and turbine section in series flow. The compressor section, combustion section, and turbine section define at a portion of an engine airflow path for the gas turbine engine. The gas turbine engine further includes one or more members extending at least partially into the engine airflow path of the gas turbine engine and one or more pressure sensor devices at least partially integrated into the one or more members extending at least partially into the engine airflow path. The one or more pressure sensor devices are configured to obtain measurements for determining a distortion condition for the gas turbine engine.
    Type: Grant
    Filed: February 2, 2016
    Date of Patent: October 6, 2020
    Assignee: General Electric Company
    Inventors: Brian Francis Nestico, Brian K. Kestner, Brandon Wayne Miller
  • Exhaust plume cooling using periodic interruption of exhaust gas flow to form ambient air entraining vortices
    Patent number: 10794329
    Abstract: An exhaust plume cooling device for cooling an exhaust gas plume to reduce deleterious heat effects on impinged and surrounding surfaces. The device is supportable in a position downstream of an exhaust nozzle of an exhaust gas plume-producing engine and configured to periodically interrupt the flow of exhaust gases by injecting fluid into the exhaust plume zone.
    Type: Grant
    Filed: December 1, 2016
    Date of Patent: October 6, 2020
    Assignee: Lockheed Martin Corporation
    Inventors: Dan J. Baruzzini, Neal David Domel, Daniel N. Miller
  • Stepped heat shield for a turbine engine combustor
    Patent number: 10794595
    Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall with a shell and a heat shield. The combustor wall defines a quench aperture therethrough. The combustor wall also defines a cavity between the shell and the heat shield. The shell defines a first aperture through which air is directed into the cavity. The heat shield includes a rail that at least partially defines a second aperture configured to direct at least some of the air within the cavity out of the combustor wall and towards the quench aperture.
    Type: Grant
    Filed: February 3, 2015
    Date of Patent: October 6, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Randal G. McKinney, Frank J. Cunha, Stanislav Kostka, Jr.
  • Gas turbine engine test stand
    Patent number: 10788398
    Abstract: A gas turbine engine test assembly includes a test apparatus having a rotor and stator and a bearing assembly having a fluid circuit providing an adjustable fluid pressure interface between the rotor and stator.
    Type: Grant
    Filed: December 23, 2016
    Date of Patent: September 29, 2020
    Assignee: Rolls-Royce Corporation
    Inventor: Jacob W. Harral