Patents Examined by Arun Goyal
  • Patent number: 11649771
    Abstract: A control system (10) for a gas turbine engine (1) having a gas generator (4) and a turbine (6) driven by the gas generator (4), is provided with: a control unit (12) to control a forward operating mode or a reverse operating mode of the gas turbine engine (1); and a supervising unit (14), operatively coupled to the control unit (12), to receive an input signal (PLA) indicative of a forward, or reverse, power request and to cause the control unit (12) to control the forward, or reverse, operating mode based on the input signal (PLA). The supervising unit (14) has an enabling stage (20) to enable a transition between the forward and reverse operating modes based on a check that a safety condition is satisfied.
    Type: Grant
    Filed: January 19, 2018
    Date of Patent: May 16, 2023
    Assignee: GE Avio S.R.L.
    Inventors: Simone Castellani, Pierpaolo Forte
  • Patent number: 11649809
    Abstract: A neutralizer suitable for use in an ion engine comprises a halogen gas source and an electrode tube comprising an inlet opening connected to the halogen gas source for supplying a halogen gas provided by the halogen gas source into the electrode tube, a discharge space for generating a plasma from the halogen gas supplied into the electrode tube, and an outlet opening for discharging the plasma generated in the discharge space and free electrons from the electrode tube. An electron emitter is arranged in the discharge space of the electrode tube, which is at least partially made of tungsten, a tungsten alloy or a tungsten composite material containing at least one of iridium, rhenium, ruthenium, rhodium and osmium.
    Type: Grant
    Filed: December 11, 2020
    Date of Patent: May 16, 2023
    Assignee: Airbus Defence and Space GmbH
    Inventors: Franz Georg Hey, Nils Gerrit Kottke, G√ľnter Kornfeld
  • Patent number: 11652397
    Abstract: A time average peak value of low frequency magnetic noise or low frequency conductive noise generated from a power supply device which drives a Hall thruster is suppressed without mass of a satellite significantly increased. A pulse width control circuit (22) of a Hall thruster power supply device (10) outputs a spread signal (58) obtained by performing spread spectrum on a pulse signal based on a control signal (54). A voltage output circuit (21) outputs output voltage (52) to a Hall thruster (50) in accordance with the spread signal (58) output by the pulse width control circuit (22).
    Type: Grant
    Filed: October 12, 2016
    Date of Patent: May 16, 2023
    Assignee: Mitsubishi Electric Corporation
    Inventors: Hiroyuki Osuga, Takayuki Hidaka, Takashi Miyamoto
  • Patent number: 11644016
    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: March 28, 2021
    Date of Patent: May 9, 2023
    Assignee: Benchmark Space Systems, Inc.
    Inventors: Mahadevan Krishnan, Katherine M. Velas
  • Patent number: 11646142
    Abstract: This application describes creating, modifying, and bending electromagnetic solitons at large scales for the various applications. An electromagnetic soliton generator system controls the magnetic soliton such that the orientation, rotation rate, pitch angle, and magnetic field strength of the solitons are modified to provide the described standing waves and generate a magnetic flux differential.
    Type: Grant
    Filed: December 6, 2019
    Date of Patent: May 9, 2023
    Inventors: Thomas Hunt Hawkins, David Hawkins
  • Patent number: 11643915
    Abstract: Embodiments of drive equipment for mobile hydraulic fracturing power units and methods for changing and controlling the drive equipment are disclosed. The mobile power units include a gas turbine engine that provides mechanical power to drive shaft which is connected to the drive equipment such that the drive equipment is driven by the engine. The drive equipment may be a hydraulic fracturing pump or an electrical generator. The drive shaft is rotated at a speed suitable for the hydraulic fracturing pump and the electrical generator includes a step up gearbox to increase a rotational speed of the drive shaft for use by the electrical generator. The drive equipment may be secured to a skid that is field changeable with a crane or a fork lift to change the drive equipment at a well pad based on the demands of the well pad.
    Type: Grant
    Filed: August 30, 2021
    Date of Patent: May 9, 2023
    Assignee: BJ Energy Solutions, LLC
    Inventors: Tony Yeung, Ricardo Rodriguez-Ramon, Joseph Foster
  • Patent number: 11629857
    Abstract: Combustors and gas turbines are provided. A combustor includes an axial centerline and an end cover. The combustor further includes at least one fuel nozzle that extends from the end cover and at is least partially surrounded by a combustion liner. The combustion liner extends between the at least one fuel nozzle and an aft frame and that defines a combustion chamber. An outer sleeve is spaced apart from and surrounds the combustion liner such that an annulus is defined therebetween. The outer sleeve defines at least one aperture. A wake energizer is mounted on the outer sleeve. The wake energizer defines at least one passage that is angled with respect to the axial centerline of the combustor. The at least one passage aligns and is in fluid communication with the at least one aperture of the outer sleeve.
    Type: Grant
    Filed: March 31, 2021
    Date of Patent: April 18, 2023
    Assignee: General Electric Company
    Inventors: Lucas John Stoia, Homayoon Feiz, Shreekrishna Rao, Emily Klara Happ
  • Patent number: 11629613
    Abstract: A method of controlling a gas turbine engine includes the steps of: detecting a shaft break event in a shaft connecting a compressor of the gas turbine engine to a turbine of the gas turbine engine; and in response to this detection, activating a shaft break mitigation system which introduces a fluid into a gas flow of the gas turbine engine downstream of the turbine, or increases an amount of a fluid being provided into the gas flow of the gas turbine engine downstream of the turbine, whereby the fluid reduces an effective area of a nozzle for the gas flow so as to reduce the mass flow rate of the gas flow through the turbine.
    Type: Grant
    Filed: January 16, 2020
    Date of Patent: April 18, 2023
    Assignee: ROLLS-ROYCE plc
    Inventor: Natalie C Wong
  • Patent number: 11614050
    Abstract: A system and method for vectoring the thrust of a supersonic, air-breathing engine. A thrust vectoring mechanism uses two asymmetrically staggered ramps; one placed at the throat, the other positioned at the exit lip of the nozzle of the engine to re-direct exhaust flow off-axis with the nozzle.
    Type: Grant
    Filed: December 12, 2018
    Date of Patent: March 28, 2023
    Inventors: Carlos F. Montes, Roger L. Davis
  • Patent number: 11608783
    Abstract: An embodiment of a torch igniter for a combustor of a gas turbine engine includes a combustion chamber oriented about an axis, a cap defining an axially upstream end of the combustion chamber, a tip defining the axially downstream end of the combustion chamber, an igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, an outlet passage defined by the igniter wall within the tip, a glow plug housing configured to receive a glow plug and allow an innermost end of the glow plug to extend into the combustion chamber, and a cooling system. The cooling system includes an air inlet formed within an exterior of the structural wall, a cooling channel forming a flow path through the structural wall at the glow plug housing, and an air passage.
    Type: Grant
    Filed: November 4, 2020
    Date of Patent: March 21, 2023
    Assignee: Delavan, Inc.
    Inventors: Jason Ryon, Lev Alexander Prociw
  • Patent number: 11608986
    Abstract: A combustor nozzle and a combustor for a gas turbine including the same are provided. The combustor nozzle may include a plurality of vanes disposed radially on an outer circumferential surface thereof, each vane including an internal cavity to which fuel is supplied, wherein the vane may include an airfoil in cross-section, wherein at least one of a pressure surface and/or a suction surface of the airfoil is disposed in a height direction thereof with a plurality of nozzle holes communicating with the cavity, wherein the vane may include a V-shaped nozzle hole including a pair of outlets on both sides of the airfoil based on a leading edge of the airfoil, wherein the V-shaped nozzle hole may form an angle (?) diverging outward with respect to a horizontal plane across the leading edge, and an acute angle (?) radially outward with respect to a vertical plane perpendicular to the horizontal plane.
    Type: Grant
    Filed: February 17, 2020
    Date of Patent: March 21, 2023
    Inventors: Alexander Myatlev, Yunyoung Doh, Borys Shershnyov
  • Patent number: 11598527
    Abstract: A method of reducing noise from a combustor of a gas turbine engine includes the steps of establishing a maximum noise limit that may be for a particular frequency range. A primary fuel flow percentage, which may be emitted from a fuel nozzle arrangement having various groupings of simplex and duplex nozzles, is then established. An immersion depth measured between an aft rim of a swirler and a distal tip of the fuel nozzles may then be reduced thereby reducing the noise amplitude.
    Type: Grant
    Filed: June 9, 2016
    Date of Patent: March 7, 2023
    Assignee: Raytheon Technologies Corporation
    Inventors: Justin M. Locke, Dennis Moura, Duane McCormick, Scott A. Liljenberg, Theodore Strickland, William Proscia
  • Patent number: 11598321
    Abstract: A Hall-effect thruster assembly includes a plurality of magnetic sources for creating a magnetic circuit. The plurality of magnetic sources are positioned between a first end and a second, opposite end of the Hall-effect thruster. The plurality of magnetic sources define a longitudinal axis extending through the first end and the second end. The first end is configured as a discharge end. A mount assembly is coupled to the second end. The mount assembly is configured to secure the plurality of magnetic sources to a spacecraft. A magnetic element is supported by the mount assembly. The magnetic element is positioned relative to the plurality of magnetic sources by the mount assembly.
    Type: Grant
    Filed: April 2, 2020
    Date of Patent: March 7, 2023
    Inventor: Jason D. Sommerville
  • Patent number: 11578682
    Abstract: A hybrid propulsion system for a small satellite package consisting of a main rocket motor containing a solid propellant with multiple oxidizer tanks positioned to direct oxidizer into the rocker motor, thereby producing a desired thrust necessary for orbit insertion and/or orbit correction. Additionally, oxidizers can serve a dual function in controlling cold fuel thrusters for attitude adjustment.
    Type: Grant
    Filed: June 27, 2019
    Date of Patent: February 14, 2023
    Assignee: California Institute of Technology
    Inventors: Ashley C. Karp, Elizabeth Jens, Jason Rabinovitch, Barry Nakazono, Antonietta Conte
  • Patent number: 11566587
    Abstract: An exemplary gas turbine engine includes a fan section including a fan rotor and at least one fan blade. A fan pressure ratio across the at least one fan blade is less than 1.45, noninclusive of the pressure across any fan exit guide vane system. The engine further includes a low-pressure compressor having a low-pressure compressor rotor that rotates together with the fan rotor at a common speed in operation, and a geared architecture that drives the low-pressure compressor rotor and the fan rotor. The geared architecture has a gear reduction ratio of greater than 2.5. The engine further includes a high-pressure compressor having a pressure ratio greater than 20, a low-pressure turbine having a pressure ratio greater than 5, and a bypass ratio greater than 10.
    Type: Grant
    Filed: March 9, 2020
    Date of Patent: January 31, 2023
    Inventors: William G. Sheridan, Michael E. McCune
  • Patent number: 11566787
    Abstract: A cartridge for attachment to the inner surface of a single-walled combustion liner of an annular combustor is provided. The cartridge includes at least one chute projecting into the combustion chamber for a counter swirl effect for improved fuel/air mixing in the combustion chamber and at least two studs projecting through associated stud holes in the liner. A method for attaching a cartridge to the inner surface of a single-walled combustion liner is also provided.
    Type: Grant
    Filed: April 6, 2020
    Date of Patent: January 31, 2023
    Inventors: Charles B. Graves, David E. B. Stone
  • Patent number: 11561007
    Abstract: A combustor liner for a gas turbine engine, the combustor liner including a panel configured to at least partially define a combustion chamber. The combustor liner further includes a shell configured to mount to the panel and form a gap between the panel and the shell. The panel includes a stud and a plurality of a stand-off pins proximate to the stud defining a cavity therebetween. The shell includes a plurality of angled impingement holes located away from the cavity but extending through the shell at an orientation such that cooling air passing through the angled impingement holes is directed towards the cavity between adjacent stand-off pins and at an acute angle relative to the stud.
    Type: Grant
    Filed: December 23, 2019
    Date of Patent: January 24, 2023
    Assignee: United Technologies Corporation
    Inventor: Fumitaka Ichihashi
  • Patent number: 11560848
    Abstract: A method to attenuate noise associated with operation of a gas turbine engine during a fracturing operation may include connecting an inlet of a first elongated plenum to an exhaust duct of the gas turbine engine. The method further may include connecting a noise attenuator to a distal end of the first elongated plenum. The noise attenuator may include first and second silencer hoods. The method also may include pivoting the first and second silencer hoods from stowed positions to operative positions so that the second silencer hood in combination with the first silencer hood define a second elongated plenum positioned to receive exhaust gas via the first elongated plenum and the exhaust duct. The first elongated plenum and the second elongated plenum may increase an effective length of the exhaust duct and may reduce sound emission associated with operation of the gas turbine engine.
    Type: Grant
    Filed: October 15, 2021
    Date of Patent: January 24, 2023
    Assignee: BJ Energy Solutions, LLC
    Inventors: Tony Yeung, Ricardo Rodriguez-Ramon, Heber Martinez-Barron
  • Patent number: 11554883
    Abstract: A system for propelling a nanosatellite, including a pair of separated electrodes defining an ignition space therebetween a power source operationally connected to the pair of separated electrodes. Also included is a liquid propellant reservoir a pump reconnected in fluidic communication with reservoir and the ignition space and an electronic controller operationally corrected to the power source and to the pump.
    Type: Grant
    Filed: June 23, 2020
    Date of Patent: January 17, 2023
    Inventors: Alexey Shashurin, Yunping Zhang, Adam Patel
  • Patent number: 11549687
    Abstract: A combustion staging system for fuel injectors of a multi-stage combustor of a gas turbine engine. The system includes plural fuel injectors, each having respective pilot and mains injection stages. It further includes a splitting unit which, to perform staging control of the combustor, receives a metered fuel flow and, for pilot and mains operation, controllably splits the received fuel flow into a pilot flow for injecting at the pilot stages of the injectors and a mains flow for injecting at the mains stages of the injectors, and for pilot-only operation, controllably splits the received fuel flow into a first part of the pilot flow for injecting at the pilot stages of a first portion of the injectors and a second part of the pilot flow for injecting at the pilot stages of a second portion of the injectors.
    Type: Grant
    Filed: June 30, 2020
    Date of Patent: January 10, 2023
    Assignee: Rolls-Royce PLC
    Inventors: Michael Griffiths, Daniel J. Bickley