Patents Examined by Ehud Gartenberg
  • Patent number: 11519334
    Abstract: An igniter for a combustor of a turbomachine includes a fuel inlet in fluid communication with a mixing plenum. The mixing plenum is positioned upstream of a mixing channel. An air inlet is in fluid communication with the mixing plenum and an ignition source is in operative communication with the mixing channel. The igniter may include a mounting flange configured for coupling the igniter to the combustor. The ignition source may be positioned proximate to a downstream end of the mixing channel and upstream of the mounting flange. The mixing channel may define a venturi shape. The venturi shape includes a converging section between an upstream end of the mixing channel and a venturi throat.
    Type: Grant
    Filed: July 31, 2017
    Date of Patent: December 6, 2022
    Assignee: General Electric Company
    Inventors: Lucas John Stoia, Yimin Huang, Abdul Khan, Thomas Edward Johnson, Heath M. Ostebee, Jayaprakash Natarajan
  • Patent number: 11512642
    Abstract: Described herein are embodiments of systems and methods for the removal of a direct drive unit (DDU) housed in an enclosure, such as a direct drive turbine (DDT) connected to a gearbox for driving a driveshaft connected to a pump for use in hydraulic fracturing operations.
    Type: Grant
    Filed: August 9, 2022
    Date of Patent: November 29, 2022
    Assignee: BJ Energy Solutions, LLC
    Inventors: Tony Yeung, Ricardo Rodriguez-Ramon, Joseph Foster, Nicholas Tew
  • Patent number: 11506383
    Abstract: The gas turbine combustor liner can delimit a combustion chamber, and have at least one monolithic ceramic block having a first face exposed to the combustion chamber and a second face opposite the first face, and a 3D fabric of ceramic fibers partially embedded inside the monolithic ceramic block, and partially extending outside the second face of the monolithic ceramic block, away from the combustion chamber.
    Type: Grant
    Filed: October 9, 2020
    Date of Patent: November 22, 2022
    Assignee: PRATT & WHITNEY CANADA CORP
    Inventor: Larry Lebel
  • Patent number: 11506120
    Abstract: Provided is a method for enabling high-density air to be efficiently manufactured without unnecessarily increasing the pressure and temperature. A method for manufacturing high-density air according to the present invention includes: mixing raw air A with fine water particles W to generate water-containing air A1 having a lower pressure than the raw air A; supplementing the water-containing air A1 with a differential pressure between the pressure of the raw air A and the pressure of the water-containing air A1; and consequently promoting vaporization of the fine water particles W in the water-containing air A1 and reducing the volume of the water-containing air A1 to manufacture high-density air A2. The density of air can be efficiently increased with this method.
    Type: Grant
    Filed: January 13, 2016
    Date of Patent: November 22, 2022
    Inventor: Takaitsu Kobayashi
  • Patent number: 11499485
    Abstract: An engine control device may comprise a processor and a memory. The engine control device may be configured to modify a fuel flow based on a density of the fuel proximate a fuel nozzle. The engine control device may include a densimeter embedded in, or disposed proximate, the engine control device. The engine control device may include a temperature sensor embedded in, or disposed proximate, the engine control device. The engine control device may be electrically coupled to a fuel valve and/or configured to modulate the fuel valve based on a density of the fuel at the fuel valve.
    Type: Grant
    Filed: February 10, 2020
    Date of Patent: November 15, 2022
    Assignee: Raytheon Technologies Corporation
    Inventors: Donald E. Grove, James K. Berry
  • Patent number: 11492971
    Abstract: An assembly is provided for a turbine engine. This assembly includes a primary duct, a bleed duct, a plurality of secondary ducts, a heat exchanger and a flow regulator. The bleed duct extends from a bleed duct inlet to a bleed duct outlet. The bleed duct inlet is fluidly coupled with the primary duct. The secondary ducts are arranged in parallel between the bleed duct outlet and the primary duct. The secondary ducts include a first duct and a second duct. The heat exchanger is configured with the second duct. The flow regulator is configured to direct at least a majority of fluid flowing through the bleed duct outlet to: (A) the first duct during a first mode of operation; and (B) the second duct during a second mode of operation.
    Type: Grant
    Filed: September 6, 2019
    Date of Patent: November 8, 2022
    Assignee: Raytheon Technologies Corporation
    Inventors: Joseph J. Sodaro, Thomas G. Phillips, Stephanie M. Polly
  • Patent number: 11486371
    Abstract: A Hall thruster includes an annular discharge region and an annular cathode concentric to the annular discharge region.
    Type: Grant
    Filed: December 19, 2017
    Date of Patent: November 1, 2022
    Assignee: AEROJET ROCKETDYNE, INC.
    Inventor: Justin Pucci
  • Patent number: 11480162
    Abstract: A pulsed metal plasma thruster (MPT) cube has a plurality of thrusters, each having a first cathode electrode and a trigger electrode separated from the first electrode by an insulator sufficient to support an initiation plasma, and a porous anode electrode positioned a separation distance from the face of all of the cathode electrodes. The cathode electrode can be either the inner electrode or the outer electrode. A power supply delivers a high voltage pulse to the trigger electrode with respect to the cathode electrode sufficient to initiate a plasma on the surface of the insulator. The plasma transfers between the anode electrode and cathode electrode of selected thrusters, thereby generating a pulse of thrust.
    Type: Grant
    Filed: April 20, 2021
    Date of Patent: October 25, 2022
    Assignee: Alameda Applied Sciences Corporation
    Inventor: Mahadevan Krishnan
  • Patent number: 11473503
    Abstract: Described herein are embodiments of systems and methods for the removal of a direct drive unit (DDU) housed in an enclosure, such as a direct drive turbine (DDT) connected to a gearbox for driving a driveshaft connected to a pump for use in hydraulic fracturing operations.
    Type: Grant
    Filed: June 24, 2022
    Date of Patent: October 18, 2022
    Assignee: BJ Energy Solutions, LLC
    Inventors: Tony Yeung, Ricardo Rodriguez-Ramon, Joseph Foster, Nicholas Tew
  • Patent number: 11459908
    Abstract: A ceramic matrix composite (CMC) component including a plurality of layers of a CMC and a directionally controllable CMC insert. The directionally controllable CMC insert is disposed in the plurality of layers of a ceramic matrix composite. The directionally controllable CMC insert includes an optimized architecture to strengthen a high stress region of the CMC component. The directionally controllable CMC insert is geometrically configured and disposed within the plurality of layers of the CMC to redirect a crack in the CMC component toward a region of low crack growth driving force. A turbomachine and method of forming a turbomachine member including a plurality of layers of a CMC and having the directionally controllable CMC insert disposed in a shaped void are additionally disclosed.
    Type: Grant
    Filed: August 31, 2018
    Date of Patent: October 4, 2022
    Assignee: General Electric Company
    Inventors: Douglas Glenn Decesare, Daniel Gene Dunn
  • Patent number: 11448140
    Abstract: Testable, redundant pneumatic control assemblies and related systems and methods are described herein. An example pneumatic control assembly described herein includes first, second, and third parallel supply channels between a compressed air supply and valve header, first, second, and third parallel vent channels between a vent and the valve header, and first, second, third, fourth, fifth, and sixth logic valves. The first and sixth logic valves are disposed in the first parallel supply channel and the first parallel vent channel, the second and third logic valves are disposed in the second parallel supply channel and second parallel vent channel, and the fourth and fifth logic valves are disposed in the third parallel supply channel and third parallel vent channel. The pneumatic control assembly also includes a first, second, and third solenoid valves to control certain ones of the logic valves.
    Type: Grant
    Filed: March 26, 2020
    Date of Patent: September 20, 2022
    Assignee: Emerson Process Management Power and Water Solutions, Inc.
    Inventors: Thomas Sweeney, Ryan Michael Purtell, Kolin Hundertmark, Michael Henry Winwood, Samuel David Onuska, Michael David Scandrol
  • Patent number: 11434821
    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: May 7, 2021
    Date of Patent: September 6, 2022
    Assignee: General Electric Company
    Inventor: Aaron Joseph Wertz
  • Patent number: 11434825
    Abstract: A method, control unit and rotating machine for determining a fuel split setting value for adjusting a fuel split setting for a combustion device, the fuel split setting defining a relation between main fuel and pilot fuel. The method includes: retrieving a first information item correlated to heating value of supplied main fuel; retrieving a second information item correlated to combustor operating condition; retrieving at least one third information item representing stability of combustion; selecting a predefined pair of minimum and maximum boundary curves for the fuel split setting from a plurality of predefined pairs based on the first and second information items, the minimum and maximum boundary curves defining a band of fuel split settings permitted for a range of second information item values; determining the fuel split setting value within the selected pair of minimum and maximum boundary curves based on the third information item.
    Type: Grant
    Filed: May 27, 2015
    Date of Patent: September 6, 2022
    Assignee: Siemens Energy Global GmbH & Co. KG
    Inventors: Varkey Alexander, Kexin Liu, Victoria Sanderson
  • Patent number: 11428168
    Abstract: A starter/generator arrangement includes a starter/generator, a power converter electrically connected to the starter/generator, and coolant circuit with a pump and a condenser in fluid communication with the power converter. The power converter is arranged to flow start mode electrical power in a first direction in a start mode and a second direction in a generate mode. The coolant circuit fluidly couples the pump to the condenser for storing heat in a coolant disposed within the coolant circuit while flowing the start mode electrical power in the first direction. Gas turbine engines and methods of cooling starter/generator arrangements are also described.
    Type: Grant
    Filed: January 6, 2020
    Date of Patent: August 30, 2022
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Debabrata Pal, Craig R. LeGros, Tom A. Utecht
  • Patent number: 11421603
    Abstract: Turbojet engine includes a fan, a compressor, a combustion chamber, and a turbine configured to rotatably drive the fan via a first reduction gear and the compressor via a second reduction gear, in which an outlet of the first reduction gear is rotatably coupled to an inlet of the second reduction gear by a reduction shaft, the reduction shaft being supported by a bearing arranged between the first reduction gear and the second reduction gear.
    Type: Grant
    Filed: September 20, 2019
    Date of Patent: August 23, 2022
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Nathalie Nowakowski, Gilles Alain Marie Charier, Kévin Morgane Lemarchand, Nicolas Jérôme Jean Tantot, Jonathan Evert Vlastuin, Henri Yesilcimen
  • Patent number: 11421877
    Abstract: A method for operating a gas turbine engine includes receiving data indicative of an operational vibration within a section of the gas turbine engine; and providing electrical power to a shaker mechanically coupled to one or more components of the section of the gas turbine engine to generate a canceling vibration to reduce or minimize the operational vibration within the section of the gas turbine engine.
    Type: Grant
    Filed: August 29, 2017
    Date of Patent: August 23, 2022
    Assignee: GENERAL ELECTRIC COMPANY
    Inventor: Daniel Edward Mollmann
  • Patent number: 11415051
    Abstract: A system for lubricating components of a gas turbine engine includes a supply pump to pump lubricant from a reservoir through a supply conduit to lubricated component. An outer body deicing circuit is fluidly coupled in series with the supply conduit. Moreover, a scavenge conduit extends from the lubricated component to the reservoir and a scavenge pump pumps the lubricant from the lubricated component through the scavenge conduit. In addition, a valve is fluidly coupled in series with the supply conduit and the scavenge conduit and a bypass conduit extends from the valve to a location on the supply conduit downstream of the deicing circuit. When the lubricant is supplied to the valve, the valve directs the lubricant flowing through the scavenge conduit into the reservoir. When the supply of lubricant to the valve is halted, the valve directs the lubricant flowing through the scavenge conduit into the bypass conduit.
    Type: Grant
    Filed: December 22, 2020
    Date of Patent: August 16, 2022
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: James John Luz, Robert Burton Brown, Thomas Bradley Kenney, Thomas Charles McCarthy, Firas Younes
  • Patent number: 11415063
    Abstract: A gas turbine engine has a first spool having a low pressure compressor section disposed forward of an air inlet along a direction of travel of the engine, and a low pressure turbine section disposed forward of the low pressure compressor section and drivingly engaged thereto. A second spool has a high pressure compressor section disposed forward of the low pressure compressor section, and a high pressure turbine section disposed forward of the high pressure compressor section and drivingly engaged thereto. The high pressure turbine section is disposed aft of the low pressure turbine section. An output drive shaft drivingly engages the low pressure turbine section and extends forwardly therefrom to drive a rotatable load. A method of operating a gas turbine engine is also discussed.
    Type: Grant
    Filed: September 15, 2016
    Date of Patent: August 16, 2022
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Keith Morgan, Robert Peluso, Ghislain Plante, Eugene Gekht, Eric Durocher, Jean Dubreuil
  • Patent number: 11415046
    Abstract: A disk engine and system configured to provide high power at a reduced axial length is disclosed herein. The disk engine includes a radial compressor, a compressor discharge manifold positioned circumferentially about compressor, a combustion chamber positioned within the discharge manifold and a radial turbine positioned radially inward of the combustion chamber.
    Type: Grant
    Filed: May 5, 2020
    Date of Patent: August 16, 2022
    Assignee: United States of America as represented by the Secretary of the Air Force
    Inventors: Brian Bohan, Marc Polanka, Bennett Staton
  • Patent number: 11408352
    Abstract: A gas turbine engine has a first spool having a low pressure compressor section in fluid communication with an air inlet, the low pressure compressor section including a first plurality of variable guide vanes therein, and a low pressure turbine section drivingly engaged to the low pressure compressor section. A second spool has a high pressure compressor section in fluid communication with the low pressure compressor section to receive pressurized air therefrom, the high pressure compressor section including a second plurality of variable guide vanes at an entry thereof, and a high pressure turbine section drivingly engaged to the high pressure compressor section, the high pressure turbine section disposed upstream of the low pressure turbine section and in fluid communication therewith. An output drive shaft drivingly engages the low pressure turbine section and is adapted to drivingly engage a rotatable load of the gas turbine engine.
    Type: Grant
    Filed: October 22, 2020
    Date of Patent: August 9, 2022
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Keith Morgan, Robert Peluso, Ghislain Plante, Eugene Gekht, Eric Durocher, Jean Dubreuil, Stephen Mah, Philippe Beauchesne-Martel