Patents Examined by Gerald L Sung
  • Patent number: 11326780
    Abstract: A resonant sound absorbing device of a gas turbine combustor includes a plurality of resonance chambers independently disposed side by side in an axial direction of the gas turbine combustor so as to communicate with a gas passage of the gas turbine combustor via acoustic holes. The plurality of resonance chambers include n related resonance chambers each satisfying: 0.9 × ? i = 1 n ? F i n ? F i ? 1.1 × ? i = 1 n ? F i n ( A ) where n is an integer of 2 or more, and Fi is a peak frequency corresponding to a maximum sound absorbing ratio of the ith related resonance chamber of the n related resonance chambers.
    Type: Grant
    Filed: February 28, 2018
    Date of Patent: May 10, 2022
    Assignee: MITSUBISHI POWER, LTD.
    Inventors: Kiyoshi Fujimoto, Taiki Kinoshita, Satoshi Mizukami, Yoshinori Wakita, Satoshi Takiguchi, Wataru Kugimiya
  • Patent number: 11326775
    Abstract: A fuel injector providing a flow of fuel having a variable swirl and/or variable effective area is disclosed. The fuel injector may have a nozzle defining a mixing chamber having an outlet proximate a centerline of the mixing chamber, a first fuel line in fluid communication with the mixing chamber and a second fuel line in fluid communication with the mixing chamber. The first fuel line may terminate in a tangential fuel inlet positioned tangential to the centerline of the nozzle, while the second fuel line may terminate in a radial fuel inlet positioned radial to the centerline of the nozzle.
    Type: Grant
    Filed: December 13, 2013
    Date of Patent: May 10, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Stephen K. Kramer
  • Patent number: 11319875
    Abstract: In a main flow passage, a first heat exchanger, a first heat storage unit, a second heat exchanger, and a second heat storage unit are connected by a heating medium flow passage. The main flow passage allows a heating medium to be circulated. A sub flow passage includes a shortened flow passage which is a part of the heating medium flow passage and branches from the heating medium flow passage between the second heat exchanger and the second heat storage unit and extends to the first heat storage unit. The sub flow passage allows circulation of the heating medium between the first heat storage unit and the second heat exchanger. A first heating means in a middle of the shortened flow passage, the first heating means heating a passing heat medium, and a switching means conducting switching between the main flow passage and the sub flow passage are provided.
    Type: Grant
    Filed: March 15, 2018
    Date of Patent: May 3, 2022
    Assignee: Kobe Steel, Ltd.
    Inventors: Yohei Kubo, Masaki Matsukuma, Yuji Matsuo, Takashi Sato, Ryo Nakamichi
  • Patent number: 11313559
    Abstract: The invention refers to a method and a device for flame stabilization in a burner system of a stationary combustion engine, preferably a stationary gas turbine, in which a flow of an air/fuel mixture is produced and being swirled to form a vortex flow to which a swirl number is assignable before entering a combustion zone in which the vortex flow of the air/fuel mixture is ignited to form a flame within a reverse flow zone caused by vortex breakdown. The swirl number perturbation driven by thermoacoustic oscillation inside the burner system is controlled by affecting the vortex flow actively before entering the combustion zone on basis of changing a flame transfer function assigned to the burner system with the proviso of minimizing pulsation amplitudes of the flame transfer function.
    Type: Grant
    Filed: February 22, 2016
    Date of Patent: April 26, 2022
    Assignee: ANSALDO ENERGIA SWITZERLAND AG
    Inventors: Fernando Biagioli, Alessandro Scarpato, Torsten Wind, Khawar Syed
  • Patent number: 11306679
    Abstract: The invention relates to an aircraft turbine engine module (10), comprising a degassing tube (14) and an ejection cone (12). The tube and the cone comprise centring means engaging together. The invention also relates to a locating and adjusting tool for assembling said module.
    Type: Grant
    Filed: October 25, 2016
    Date of Patent: April 19, 2022
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventor: Samuel Louis-Marie Bernard
  • Patent number: 11305885
    Abstract: A system and method for adaptively controlling a cooldown cycle of an auxiliary power unit (APU) that is operating and rotating at a rotational speed includes reducing the rotational speed of the APU to a predetermined cooldown speed magnitude that ensures combustor inlet temperature has reached a predetermined temperature value, determining, based on one or more of operational parameters of the APU, when a lean blowout of the APU is either imminent or has occurred, and when a lean blowout is imminent or has occurred, varying one or more parameters associated with the shutdown/cooldown cycle.
    Type: Grant
    Filed: January 10, 2019
    Date of Patent: April 19, 2022
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Robert Mallette, Bradley Volkmann
  • Patent number: 11300075
    Abstract: A mechanical connection system is provided that includes a ceramic skin panel, at least one bushing, and at least one bolt. The ceramic skin panel includes a first surface, a second surface, and at least one aperture extending between the first surface and the second surface. The aperture has an axial centerline, a chamfered portion contiguous with the first surface, and an axial portion contiguous with the second surface. The chamfered portion includes a tapered surface disposed at a first angle such that a line extending along the tapered surface intersects the axial centerline at a plane of the second surface. The bushing has a housing and a collar. The housing is configured to mate with the chamfered portion of the aperture disposed within the ceramic skin panel. The collar is configured for engagement with the housing.
    Type: Grant
    Filed: March 12, 2019
    Date of Patent: April 12, 2022
    Assignee: Rohr, Inc.
    Inventors: Richard S. Alloway, Vijay V. Pujar, Jinqiu Lu, Adam Saunders, Gary E. Bowman
  • Patent number: 11300054
    Abstract: Systems and methods for controlling fuel flow to an engine during start are provided. Fuel is caused to be injected into a combustor of the engine according to a first fuel schedule defining a minimum fuel flow limit required to achieve light-off of the engine, the minimum fuel flow limit set at an initial value. Following light-off of the engine, at least one operating parameter of the engine is monitored. Based on the at least one operating parameter, occurrence of flameout in the engine is detected. In response to detecting occurrence of flameout in the engine, the minimum fuel flow limit is increased from the initial value to a first value to obtain an adjusted fuel schedule, and fuel is caused to be injected into the combustor according to the adjusted fuel schedule.
    Type: Grant
    Filed: November 8, 2018
    Date of Patent: April 12, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Nicolas Des Roches-Dionne, Sylvain Lamarre, Simon Lopez
  • Patent number: 11300002
    Abstract: A duct for a gas turbine engine, the duct has a wall defining a flow passage for an airflow, the wall defining a baseline surface, the duct comprising an off-take port for drawing a portion of the airflow out of the duct, the off-take port including a projected portion projecting away from the baseline surface into the flow passage, a conduit opening defined within the projected portion for receiving the portion of the airflow, and an off-take conduit communicating with the conduit opening for directing the portion of the airflow away from the duct, the projected portion having a hump upstream of the conduit opening relative to a direction of the airflow and a scoop downstream of the opening relative to the direction of the airflow.
    Type: Grant
    Filed: December 9, 2019
    Date of Patent: April 12, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Ivan Sidorovich Paradiso, Daniel Alecu
  • Patent number: 11293292
    Abstract: A gas turbine engine includes a compressor section and a combustion section with a scroll, a scroll baffle, a combustor, and a combustor case. The scroll defines an interior scroll flow path. The scroll baffle surrounds the scroll to define a scroll cooling passage. The combustor case surrounds the combustor and the scroll baffle to define a collector space. Moreover, the engine includes a turbine section with a turbine rotor and a turbine rotor blade shroud that includes a shroud cooling passage. The compressor flow path is fluidly connected to the scroll for cooling the scroll. Also, the scroll cooling passage is fluidly connected to the shroud cooling passage for cooling the turbine rotor blade shroud. Furthermore, the shroud cooling passage is fluidly connected to the collector space. Flow from the collector space flows into the combustor, along the interior scroll flow path, toward the turbine rotor.
    Type: Grant
    Filed: January 7, 2020
    Date of Patent: April 5, 2022
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Jason Smoke, David K. Jan, Mark Matwey
  • Patent number: 11293377
    Abstract: A thrust reverser for a turbojet engine nacelle includes thrust reversal cascade vanes arranged about an annular flow duct having a stationary front casing, at least one movable cover moving backwards into a thrust reversal open position, and tilting flaps connected by rear pivots to the movable cover, which, in an open position, tilt and thereby at least partially close the annular flow duct. The cascade vanes move backwards with the movable cover, in that, in the closed position, the tilting flaps and the cascade vanes are arranged outside the stationary casing, and each tilting flap is connected to the stationary casing by slides which cause the tilting flaps to tilt when the movable cover moves backwards.
    Type: Grant
    Filed: March 2, 2020
    Date of Patent: April 5, 2022
    Assignee: Safran Nacelles
    Inventor: Loïc Hervé André Le Boulicaut
  • Patent number: 11293354
    Abstract: A gas turbine engine includes a main compressor section, a combustor, and a main turbine section. A fuel pump delivers fuel to the combustor. A tap taps air compressed by the main compressor section, and is connected for delivering the tapped air through a first heat exchanger and to a boost compressor. Air downstream of the boost compressor is connected to cool a component. Driving compressed air is connected to be delivered to a power turbine. The power turbine is connected to drive both the boost compressor and the fuel pump.
    Type: Grant
    Filed: January 17, 2020
    Date of Patent: April 5, 2022
    Assignee: Raytheon Technologies Corporation
    Inventor: Neal R. Herring
  • Patent number: 11293375
    Abstract: An ejector assembly includes a primary nozzle in fluid communication with a primary fluid inlet, a secondary nozzle in fluid communication with a secondary fluid inlet, the primary nozzle being oriented concentrically within the secondary nozzle and the secondary nozzle having a venturi downstream of the primary nozzle, and the primary nozzle having a variable cross-sectional area.
    Type: Grant
    Filed: February 12, 2020
    Date of Patent: April 5, 2022
    Assignee: General Electric Company
    Inventors: Arvind Namadevan, Hari Shanker Thakur, Jeffrey Douglas Rambo, Arnab Sen, Siddhartha Pal
  • Patent number: 11286881
    Abstract: A gas turbine engine system includes a gas turbine engine having a fan bypass duct, a heat exchanger system, and a flow transfer unit configured to selectively allow or preclude flow between the fan bypass duct and the heat exchanger system. A controller is coupled to and configured to vary the state of one or more of a fan exit nozzle, a heat exchanger exit nozzle, and a flow control valve controlling flow between the fan bypass duct and the heat exchanger system.
    Type: Grant
    Filed: October 16, 2019
    Date of Patent: March 29, 2022
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventors: Douglas Boyd, Douglas D. Dierksmeier, Douglas J. Snyder, Graham Burkholder, William B. Bryan
  • Patent number: 11286851
    Abstract: A gas turbine engine configured to combust, by means of a combustor, a compressed air obtained through compression by a compressor, and drive a turbine with use of high-temperature and high-pressure combustion gas generated by the combustion, the gas turbine engine including: a plurality of air passages through which different portions in the gas turbine engine communicate with one another; and a switching device configured to switch air flow paths between the plurality of air passages, wherein the plurality of air passages are each formed by an air pipe disposed outside a compressor casing, and the switching device is mounted to an outer surface of the compressor casing via a heat insulation member.
    Type: Grant
    Filed: June 14, 2019
    Date of Patent: March 29, 2022
    Assignee: KAWASAKI JUKOGYO KABUSHIKI KAISHA
    Inventors: Satoshi Nakayama, Akihisa Oka, Hiroki Seike
  • Patent number: 11286886
    Abstract: A distributed fuel module includes a fuel pressure vessel with a gas port and a fuel port, a hydraulic circuit breaker connected to the fuel port, and a gaseous circuit breaker. The gaseous circuit breaker is connected to the gas port, is fluidly coupled to the hydraulic circuit breaker through the fuel pressure vessel, and is cooperatively associated with the gaseous circuit breaker to isolate the fuel pressure vessel from a compressed gas header and a fuel header according to pressure differential within the hydraulic circuit breaker and pressure differential within the gaseous circuit breaker. Power modules and methods of controlling fuel flow in fuel modules are also described.
    Type: Grant
    Filed: April 14, 2019
    Date of Patent: March 29, 2022
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventor: Richard A. Himmelmann
  • Patent number: 11286878
    Abstract: A propulsion unit includes a gas turbine engine arranged along an axis and an exhaust system coupled to the gas turbine engine. The gas turbine engine includes an engine core configured to discharge a core flow and a fan configured to be driven by the engine core to discharge a bypass flow. The exhaust system receives the mixed bypass and core flows from the gas turbine engine.
    Type: Grant
    Filed: March 31, 2020
    Date of Patent: March 29, 2022
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Cornoration
    Inventors: Todd S. Taylor, David L. Sutterfield, Jack D. Petty, Andrew Sanderson, Bryan H. Lerg
  • Patent number: 11280267
    Abstract: A gas turbine engine according to the present disclosure includes, among other things, a fan section having a plurality of fan blades, the plurality of fan blades having a peak tip radius Rt and an inboard leading edge radius Rh at a first inboard boundary of a first flowpath, and a core engine including a first turbine configured to drive a first compressor, and a fan drive turbine configured to drive the fan section.
    Type: Grant
    Filed: August 31, 2020
    Date of Patent: March 22, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Frederick M. Schwarz, William G. Sheridan
  • Patent number: 11280214
    Abstract: A gas turbine engine component includes an exterior pressure side with a plurality of cooling holes located in the exterior pressure side. A relief cut surrounds at least one of the plurality of cooling holes.
    Type: Grant
    Filed: October 8, 2015
    Date of Patent: March 22, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Jesse M. Carr, Bryan P. Dube
  • Patent number: 11280215
    Abstract: An engine component assembly includes a first engine component having a hot surface in thermal communication with a hot combustion gas flow and a cooling surface with at least one cavity. A second engine component is spaced from the cooling surface, and includes at least one cooling aperture. The cooling aperture is arranged such that cooling fluid impinges on the cooling surface at an angle.
    Type: Grant
    Filed: October 28, 2015
    Date of Patent: March 22, 2022
    Assignee: General Electric Company
    Inventors: Robert Frederick Bergholz, Jason Randolph Allen, Robert David Briggs, Kevin Robert Feldmann, Curtis Walton Stover, Zachary Daniel Webster, Fernando Reiter