Patents Examined by Ted Kim
  • Patent number: 10704466
    Abstract: Vehicles, such as aircraft, may include turbine-based combined cycle power plants (TBCC) for power to achieve high-mach speeds. Cooling systems for such TBCC may include a turbine-generator arranged to be driven for rotation by ambient air to reduce the temperature of the ambient air while providing electric power for use under cocooning of a primary gas turbine engine in favor of a scramjet engine during high-mach travel.
    Type: Grant
    Filed: January 29, 2018
    Date of Patent: July 7, 2020
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventor: Douglas D. Dierksmeier
  • Patent number: 10662874
    Abstract: A combustion module of a turbine engine, in particular of an aircraft, is configured for carrying out constant-volume combustion. The module includes a plurality of combustion chambers angularly distributed in a regular manner around an axis. Each chamber has an intake port for pressurized gas and an exhaust port for combustion gases. Each intake/exhaust port is configured to be opened or closed by a corresponding common rotating intake/exhaust valve which is coaxial with the axis.
    Type: Grant
    Filed: January 25, 2016
    Date of Patent: May 26, 2020
    Assignee: SAFRAN
    Inventor: Matthieu Leyko
  • Patent number: 10634053
    Abstract: A gas turbine engine installed on an aircraft includes a fan rotor, a turbine rotor, a gearbox, an auxiliary pump, and an electric motor. The gearbox couples the fan rotor to the turbine rotor, the turbine rotor being adapted to drive the fan rotor via the gearbox. The auxiliary pump is configured to circulate lubricating fluid in an auxiliary lubrication system and supplies the gearbox. The electric motor is configured to receive electricity when the aircraft is parked an adapted to drive the auxiliary pump such that the auxiliary pump circulates lubricating fluid while the aircraft is parked.
    Type: Grant
    Filed: December 21, 2015
    Date of Patent: April 28, 2020
    Assignee: United Technologies Corporation
    Inventors: Frederick M. Schwarz, Michael E. McCune
  • Patent number: 10627111
    Abstract: A fuel mixer for mixing a fuel and an oxidizer prior to detonation in a rotating detonation engine includes a combustion channel configured to transport a final mixture of the fuel and the oxidizer for combustion. The fuel mixer also includes a mixture channel positioned upstream from the combustion channel and configured to transport a first mixture having at least some of the fuel and at least some of the oxidizer. The fuel mixer also includes a secondary outlet positioned upstream from the combustion channel and configured to output a supplemental mixture of the fuel and the oxidizer that includes at least one of the fuel or the oxidizer such that the first mixture and the supplemental mixture combine in the combustion channel to form the final mixture.
    Type: Grant
    Filed: March 27, 2017
    Date of Patent: April 21, 2020
    Assignee: UNITED TECHNOLOGIES COPRORATION
    Inventors: Adam Takashi Holley, Christopher Britton Greene, Peter A T Cocks
  • Patent number: 10584633
    Abstract: Disclosed is a semi-closed cycle turbine engine power system, operating with air, enriched air, or oxygen as the oxidizer, is made non-emissive via the semi-closed cycle, in a manner which produces saleable CO2 product at pressure. In an embodiment of the present disclosure, the system includes, among other elements, an oxidizer supply subsystem for producing an oxidizer and a turbine engine. The oxidizer supply subsystem provides at least a portion of the oxidizer produced by the oxidizer supply sub-system to a main compressor stage of the turbine engine. A fuel supply system is also included for providing fuel to turbine engine. Operation of the turbine engine produces power and an exhaust gas. At least a portion of the exhaust gas is recirculated via a recirculation subsystem to the main compressor stage of the turbine engine.
    Type: Grant
    Filed: August 29, 2013
    Date of Patent: March 10, 2020
    Assignee: Enhanced Energy Group LLC
    Inventor: Paul M. Dunn
  • Patent number: 10557438
    Abstract: A pulse combustor system for efficiently operating a pulse combustor. The pulse combustor system includes the pulse combustor and a duct. The pulse combustor has a combustion chamber defining an internal space, a conduit having a first end in fluid communication with the internal space and a second end in fluid communication with an environment outside of the pulse combustor system, and a fuel injector configured to inject fuel into the internal space of the combustion chamber. The duct has two openings, with one opening disposed adjacent to the second end of the conduit. The pulse combustor system has an average operating frequency, and the duct has a length that is about one quarter of a wavelength corresponding to the average operating frequency. The pulse combustor and the duct each has a central longitudinal axis, and the two axes are substantially aligned.
    Type: Grant
    Filed: December 16, 2016
    Date of Patent: February 11, 2020
    Assignee: NORTH AMERICAN WAVE ENGINE CORPORATION
    Inventor: Daanish Maqbool
  • Patent number: 10550767
    Abstract: A method of installing a segment of a recuperator within an exhaust duct of a gas turbine engine, including positioning the segment such that its exhaust inlet is in fluid flow communication with the turbine section and its exhaust outlet is adapted to deliver an exhaust flow to atmosphere, engaging its air inlet to a plenum in fluid flow communication with the compressor discharge, and engaging its air outlet to another plenum containing the combustor. One of engaging the air inlet and engaging the air outlet includes forming a rigid connection providing sealed fluid flow communication with the corresponding plenum, and the other of engaging the air inlet and engaging the air outlet includes forming a floating connection providing sealed fluid flow communication with the corresponding plenum. The floating connection allows relative movement of the segment within the exhaust duct.
    Type: Grant
    Filed: June 21, 2016
    Date of Patent: February 4, 2020
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Andreas Eleftheriou, David Menheere, Daniel Alecu
  • Patent number: 10544802
    Abstract: A compressor section for a gas turbine engine according to an example of the present disclosure includes, among other things, a low pressure compressor including a plurality of rotor blades arranged about an axis, a high pressure compressor, and a core flowpath passing through the low pressure compressor. The core flowpath at the low pressure compressor defines an inner diameter and an outer diameter relative to the axis. The outer diameter has a slope angle relative to the axis.
    Type: Grant
    Filed: March 30, 2016
    Date of Patent: January 28, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Lisa I. Brilliant, Becky E. Rose, Yuan Dong, Stanley J. Balamucki
  • Patent number: 10544735
    Abstract: An engine, a power generation system, and methods of manufacturing and using the same are disclosed. The engine includes a detonation/combustion chamber configured to detonate a fuel and rotate around a central rotary shaft extending from the chamber, a fuel supply inlet configured to provide the fuel to the chamber, an air supply channel configured to supply air to the chamber, at least two rotating arms extending radially from the chamber and configured to exhaust gases from detonating the fuel in the chamber and provide a rotational thrust and/or force, and a mechanical work unit configured to receive at least part of the rotational thrust and/or force. Each of the rotating arms has an exhaust nozzle at a distal end thereof, the exhaust nozzle being at or having an angle configured to provide the rotational thrust and/or force.
    Type: Grant
    Filed: February 18, 2016
    Date of Patent: January 28, 2020
    Inventor: Brent Wei-Teh Lee
  • Patent number: 10527284
    Abstract: The present invention relates to dampers for gas turbines and, for example, to a compensation assembly for a damper of a gas turbine for reducing the pulsations occurring in the combustion chamber. The damper can include a resonator cavity with a neck tube in flow communication with the interior of the combustion chamber, wherein the compensation assembly includes a spherical joint associated to the neck tube and configured to allow relative rotation between the combustion chamber and the resonator cavity, and having a bulb portion disposed around the neck tube and a spherical socket configured to internally host the bulb portion, wherein the spherical socket can have a top collar portion and a bottom collar portion connected to each other.
    Type: Grant
    Filed: December 10, 2015
    Date of Patent: January 7, 2020
    Assignee: ANSALDO ENERGIA SWITZERLAND AG
    Inventors: Karolina Krystyna Sobol, Christoph Welti, Urs Benz
  • Patent number: 10526965
    Abstract: A dynamic pressure exchanger configured for a combustion process includes a seal plate and a rotor assembly. The rotor assembly is mounted for rotation relative to the seal plate about a central axis of the dynamic pressure exchanger.
    Type: Grant
    Filed: April 29, 2016
    Date of Patent: January 7, 2020
    Assignee: Rolls-Royce Corporation
    Inventor: Masayoshi Shimo
  • Patent number: 10519857
    Abstract: An assembly for a gas turbine engine is arranged to rotate about a central axis of the gas turbine engine. The assembly includes a disk formed to include a plurality of apertures. The disk is operable to transfer rotational energy.
    Type: Grant
    Filed: October 24, 2016
    Date of Patent: December 31, 2019
    Assignee: Rolls-Royce Corporation
    Inventors: Charles W. Johns, Emanuel Papandreas
  • Patent number: 10513988
    Abstract: A turbomachine fuel circuit including: a low pressure pump; a high pressure pump; a low pressure conduit connecting the low pressure pump to the high pressure pump; a high pressure conduit supplied by the high pressure pump, in which a component is arranged; a mechanism for testing operation of the component; a check valve capable of closing off a segment of the conduit when the pressure in the low pressure conduit is less than a predetermined threshold value; and the testing mechanism is capable of detecting that the check valve at least partly closes off the segment.
    Type: Grant
    Filed: April 12, 2012
    Date of Patent: December 24, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Nicolas Potel, Nicolas Alain Bader
  • Patent number: 10487752
    Abstract: An overthrust protection system for an aircraft engine. The system comprises an engine overspeed protection unit comprising overspeed logic and an overspeed solenoid valve controlled by the overspeed logic, the overspeed logic configured to energize the overspeed solenoid valve for removing fuel flow to the engine upon detection of an overspeed condition of the aircraft engine; and an overthrust controller coupled to the overspeed protection unit and configured to measure engine thrust and to detect an overthrust condition when an engine thrust threshold has been exceeded, and configured to trigger energizing of the overspeed solenoid valve upon detection of the overthrust condition and an aircraft-on-ground condition.
    Type: Grant
    Filed: March 11, 2015
    Date of Patent: November 26, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Janusz Fiedler, Tatjana Pekovic, Dave Sellors, Amandeep Singh Chahal
  • Patent number: 10480420
    Abstract: A method for operating a power plant may include, during shutdown of a turbine, controlling a damper to move from a first position directing turbine exhaust to enter a heat recovery system to a second position to allow the turbine exhaust to enter a bypass stack and block the turbine exhaust to the heat recovery system. While the position of the damper is maintained in the second position, fired shutdown of the turbine may be performed. In response to instructions to start the turbine, air flow in an exhaust duct for a predetermined period of time is generated, and after generating the air flow for the predetermined period of time, the turbine may be started without performing a purge sequence for the heat recovery system. After starting the turbine, the damper may be controlled between the second position and the first position.
    Type: Grant
    Filed: March 17, 2017
    Date of Patent: November 19, 2019
    Assignee: General Electric Company
    Inventors: Myriam Couchot, Christian Solacolu, Pierre Beaufrere
  • Patent number: 10473032
    Abstract: The invention concerns a fuel system (1) for a turbomachine comprising: —a control circuit (9a), —a main circuit (9b), —a flow rate regulator (2), suitable for regulating the flow of fuel in the control circuit (9a) and in the main circuit (9b) depending on the speed of the turbomachine, and —a drain tank (4) being designed to draw fuel from, store fuel in and drain fuel into the main circuit (9b) on the basis of the pressure difference between the main circuit (9b) and the tank (5) or the high-pressure pump (6) to which it is connected.
    Type: Grant
    Filed: September 1, 2014
    Date of Patent: November 12, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Clement Bernard, Loic Pora, Sebastien Chalaud
  • Patent number: 10465557
    Abstract: A magnetic squeeze film damper system comprises a bearing assembly having an outer race with a first outer surface and a first inner surface and a bearing located along the first inner surface. The system further comprises a squeeze film damper housing having a second outer surface and a second inner surface that is contiguous with the first outer surface. A channel having a forward end and an aft end is defined within the housing along the second inner surface, the channel bordered by the first outer surface. The system further includes a first seal gland located along the forward end of the channel and a second seal gland located along the aft end of the channel. Both seal glands comprise a reservoir for holding a magneto-rheological fluid, the reservoir encased in an elastomer. At least one electromagnet is arranged in close proximity to each of the seal glands.
    Type: Grant
    Filed: September 1, 2015
    Date of Patent: November 5, 2019
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventors: Andrew D. Copeland, Donald W. Burns, Stanford O. Clemens, Alan B. Cookerly
  • Patent number: 10465538
    Abstract: A gas turbine engine having a forward thrust mode and a reverse thrust mode is provided. The gas turbine engine includes a variable pitch fan configured for generating forward thrust in the forward thrust mode of the engine and reverse thrust in the reverse thrust mode of the engine. The engine also includes a fan cowl surrounding the variable pitch fan, wherein the fan cowl forms a bypass duct for airflow generated by the fan. The fan cowl includes an aft edge that defines a physical flow area of the bypass duct, and a deflection device configured for deflecting airflow near the aft edge, wherein the deflection device is configured for operation in the reverse thrust mode of the engine. The physical flow area of the bypass duct at the aft edge remains the same in the forward thrust mode of the engine and in the reverse thrust mode of the engine.
    Type: Grant
    Filed: October 2, 2015
    Date of Patent: November 5, 2019
    Assignee: General Electric Company
    Inventors: Darek Tomasz Zatorski, Patrick John Lonneman, Alan Roy Stuart
  • Patent number: 10450078
    Abstract: An adaptive aircraft engine including a first, inner bypass duct inside a core engine of the aircraft engine and a second, outer bypass duct at least partially surrounding the first bypass duct, and adaption means, in particular adjustable nozzles for altering a flowed-through cross-section of the core engine with the first bypass duct and for altering the flowed-through cross-section of the second bypass duct depending on the flying speed. An aircraft having at least one adaptive aircraft engine is also provided.
    Type: Grant
    Filed: May 31, 2016
    Date of Patent: October 22, 2019
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Dimitrie Negulescu
  • Patent number: 10443493
    Abstract: A wave rotor assembly includes a wave rotor combustor and an exit duct. The wave rotor combustor includes an aft plate formed to include an exit port and a rotor drum mounted for rotation relative to the aft plate. The rotor drum is formed to include a plurality of rotor passages arranged to align with the exit port during rotation of the rotor drum. The exit duct is coupled to the aft plate and defines a passage arranged to receive exhaust gasses flowing through the exit port.
    Type: Grant
    Filed: February 11, 2016
    Date of Patent: October 15, 2019
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventors: Calvin W. Emmerson, Philip H. Snyder