Patents Examined by Todd E. Manahan
  • Motor and fuel-powered hybrid system for a rocket thruster
    Patent number: 11598288
    Abstract: A motor and fuel-powered hybrid system of a rocket thruster is disclosed, which mainly provides power through a motor and a fluid fuel injector. In particular, at the beginning stage of the rocket lift-off, the motor drives the compressor to provide power to send the rocket into air. When the speed and height of the rocket gradually increase, the fuel is ignited to give power to keep propelling the rocket, thereby reducing the fluid fuel that needs to be carried on the rocket, increasing the rocket's loading space and enhancing the carrying capacity.
    Type: Grant
    Filed: February 22, 2022
    Date of Patent: March 7, 2023
    Assignee: Taiwan Innovative Space, Inc.
    Inventor: Yen-Sen Chen
  • Systems and methods to enhance intake air flow to a gas turbine engine of a hydraulic fracturing unit
    Patent number: 11598264
    Abstract: Systems and methods to increase intake air flow to a gas turbine engine of a hydraulic fracturing unit when positioned in an enclosure may include providing an intake expansion assembly to enhance intake air flow to the gas turbine engine. The intake expansion assembly may include an intake expansion wall defining a plurality of intake ports positioned to supply intake air to the gas turbine engine. The intake expansion assembly also may include one or more actuators connected to a main housing of the enclosure and the intake expansion assembly. The one or more actuators may be positioned to cause the intake expansion wall to move relative to the main housing between a first position preventing air flow through the plurality of intake ports and a second position providing air flow through the plurality of intake ports to an interior of the enclosure.
    Type: Grant
    Filed: May 13, 2022
    Date of Patent: March 7, 2023
    Assignee: BJ Energy Solutions, LLC
    Inventors: Tony Yeung, Ricardo Rodriguez-Ramon, Joseph Foster
  • Liquid fuel steam purge system and method for gas turbine engine
    Patent number: 11598266
    Abstract: A system is provided with an ejector having an outer wall extending circumferentially about a flow path, wherein the outer wall has a throat section along the flow path, and a diverging section downstream from the throat section along the flow path. The ejector includes a gas inlet configured to supply a gas into the flow path, and a water inlet configured to supply water into the flow path. The ejector is configured to produce steam in response to mixing of the water and the gas along the flow path. The system also includes a controller configured to control flows of the gas and the water to produce the steam for a steam purge of a liquid fuel circuit.
    Type: Grant
    Filed: December 21, 2020
    Date of Patent: March 7, 2023
    Assignee: General Electric Company
    Inventors: Jose Francisco Aguilar, Francisco Javier Gomez
  • Method for operating a power plant
    Patent number: 11591955
    Abstract: A method for operating a power plant having a gas turbine, a heat recovery steam generator, a steam turbine, an auxiliary heat source, and a control system, wherein the method includes controlling the power plant such that the heat recovery steam generator receives an input of heat from the gas turbine; determining the gas turbine is operating at its maximum capacity or at an upper end of its control range and the power plant is operating at less than a target value for a power plant capacity; determining a target pressure value immediately upstream of the steam turbine, wherein the target pressure value is derived from a primary pressure for the steam turbine and a steam turbine capacity for the steam turbine; based upon the target pressure value, controlling the heat store to release heat into the heat recovery steam generator to achieve the predefined power plant capacity.
    Type: Grant
    Filed: June 3, 2019
    Date of Patent: February 28, 2023
    Assignee: Siemens Energy Global GmbH & Co. KG
    Inventors: Michael Henning, Wolfgang Wiesenmüller, Maria Zeis
  • Method and system for thrust reverser operation
    Patent number: 11591985
    Abstract: There are described a system and method for operating a thrust reverser of an aircraft engine, the thrust reverser having a deployed state and a stowed state. The method comprises placing the thrust reverser in the stowed state when the thrust reverser is in the deployed state, a thrust lever associated with the engine is in a forward position, and the engine is rotating at a speed below an idle speed, wherein hydraulic pressure for stowing the thrust reverser is provided by a pump driven by the engine rotating at the speed below the idle speed.
    Type: Grant
    Filed: October 21, 2020
    Date of Patent: February 28, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Hamza Assi, Yusuf Syed, Ioan Sabau
  • Turbomachine with electric machine comprising a rotor ring attached to the fan
    Patent number: 11591987
    Abstract: An aircraft turbomachine, including a fan that is able to rotate inside a casing, and an electric machine including a rotor secured to the fan and a stator secured to the casing, wherein the rotor of the electric machine includes a ring that is able to rotate inside the stator, which is linked by arms to a cone mounted upstream from the fan.
    Type: Grant
    Filed: October 25, 2019
    Date of Patent: February 28, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Caroline Marie Frantz, Gilles Alain Marie Charier, Loic Paul Yves Guillotel, Vincent Francois Georges Millier
  • Hybrid transmission on propeller gearbox
    Patent number: 11591971
    Abstract: A gearbox assembly for a gas turbine engine includes a planetary gear set comprising a sun gear, a planet gear, and a ring gear, the sun gear configured for connection to a first drive shaft of the gas turbine engine and the ring gear configured for connection to a second drive shaft of the gas turbine engine, and an electric machine assembly comprising an input and an electric machine. The electric machine comprising a rotor coupled to the input and a stator fixedly positioned within the gearbox assembly, the input of the electric machine assembly coupled to one of the sun gear, the ring gear, or the planet gear of the planetary gear set.
    Type: Grant
    Filed: February 11, 2021
    Date of Patent: February 28, 2023
    Assignee: GE AVIO S.R.L.
    Inventors: Marco Garabello, Alessio Gargioli, Fabrizio Bussi, Giuseppe Argentieri, Salvatore Garofalo
  • Oil cooling system for aircraft engine
    Patent number: 11591964
    Abstract: An oil cooling system for an aircraft engine, a bypass valve and an associate method of cooling aircraft engine oil are provided. The oil cooling system includes a heat exchanger having an inlet and an outlet. The inlet is in fluid communication with a first oil conduit to receive a first oil flow from the first oil conduit. The heat exchanger facilitates heat transfer from the first oil flow to another fluid. A flow restrictor defining a constriction is operatively disposed to restrict the first oil flow through the heat exchanger. A second oil conduit receives the first oil flow from the heat exchanger. A bypass oil passage provides fluid communication between the first oil conduit and the second oil conduit to allow a second oil flow received from the first oil conduit to flow to the second oil conduit and bypass the heat exchanger.
    Type: Grant
    Filed: June 17, 2021
    Date of Patent: February 28, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Andrew Walz, Ritchie Domingo
  • Multi-flow cooling circuit for gas turbine engine flowpath component
    Patent number: 11591915
    Abstract: A flowpath component for a gas turbine engine includes a body having a leading edge and a trailing edge. A first exterior wall connects the leading edge to the trailing edge and a second exterior wall connects the leading edge to the trailing edge. At least one first internal cooling passage has a first inlet at a first end of the body. At least one second internal cooling passage has a second inlet at a second end of the body. The at least one first internal cooling passage is isolated from the at least one second internal cooling passage.
    Type: Grant
    Filed: September 30, 2019
    Date of Patent: February 28, 2023
    Assignee: Raytheon Technologies Corporation
    Inventors: Renee Behlman, Tracy Propheter-Hinckley, Raymond Surace, Matthew Devore
  • Internal manifold for multipoint injection
    Patent number: 11585275
    Abstract: A multipoint injection system includes a manifold with a plurality of flow passages defined through the manifold in the circumferential direction. The flow passages are spaced apart from one another in an axial direction. A plurality of feed arms extends radially inward from the manifold. Feed arm portions of the flow passages extend through each of the feed arms to respective outlets. The feed arm portions of the flow passages are within the axial width of the manifold. A plurality of injection nozzles are included, each in fluid communication with a respective one of the outlets. Each injection nozzle includes an air passage therethrough with an air inlet. The feed arms each follow a path that is circumferentially offset from the air inlets so each of the feed arms is clear from a flow path directly upstream in the axial direction of each of the air inlets.
    Type: Grant
    Filed: March 5, 2021
    Date of Patent: February 21, 2023
    Assignee: Collins Engine Nozzles, Inc.
    Inventors: Jason A. Ryon, Lev A. Prociw, Gregory A. Zink, Joseph Samo
  • Aircraft heat exchangers
    Patent number: 11585273
    Abstract: A turbine engine heat exchanger has: a manifold having a first face and a second face opposite the first face; a plurality of first plates along the first face, each first plate having an interior passageway; and a plurality of second plates along the second face, each second plate having an interior passageway. A first flowpath passing through the interior passageways of the first plates, the manifold, and the interior passageways of the second plates.
    Type: Grant
    Filed: December 17, 2020
    Date of Patent: February 21, 2023
    Assignee: Raytheon Technologies Corporation
    Inventors: James F. Wiedenhoefer, Russell J. Bergman, William P. Stillman, Patrick M. Hart
  • Self compensating rocket engine enhancement
    Patent number: 11585296
    Abstract: An annular ablative gas blocking device provides for automatic altitude compensation of a rocket engine exhaust plume. The nozzle is over expanded at low level launch altitudes and near optimally expanded at the highest altitude at the terminal burnout or staging altitude of the rocket engine. The ablative gas blocking device in the nozzle exit mitigates low altitude launch effects of an over expanded nozzle and inhibits external atmospheric air entrance into the nozzle at launch. The gas blocking means ablatively erodes away from plume impingement as the rocket ascends in a pre-programmed manner to achieve optimum area expansion ratio at all altitudes.
    Type: Grant
    Filed: January 14, 2021
    Date of Patent: February 21, 2023
    Inventor: Herbert U. Fluhler
  • Rocket engine with integrated combustor head and turbopump
    Patent number: 11585295
    Abstract: The present disclosure relates to a rocket engine, and more particularly, a rocket engine with an integrated combustor head and turbopump in which a turbopump of the rocket engine is formed integrally with a combustor head.
    Type: Grant
    Filed: December 22, 2021
    Date of Patent: February 21, 2023
    Assignee: KOREA AEROSPACE RESEARCH INSTITUTE
    Inventors: Keum-Oh Lee, Byoungjik Lim, Cheulwoong Kim
  • Environmental control system
    Patent number: 11577841
    Abstract: A method and system for controlling fresh air flow into a controlled environment are disclosed herein. The method comprises: measuring, using a sensor, a predetermined property in the controlled environment; estimating, by a controller, a number of people inside the controlled environment based on the measured property, and setting, by the controller, a rate of fresh air flow to the controlled environment based at least in part on the estimated number of people inside the controlled environment.
    Type: Grant
    Filed: December 18, 2019
    Date of Patent: February 14, 2023
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Giusi Quartarone, Catherine Thibaud
  • Engine family platform design
    Patent number: 11578663
    Abstract: A method of providing an engine family includes providing a first engine having a low pressure turbine driving a low pressure compressor at a first speed ratio, and a high pressure turbine driving a high pressure compressor. The method includes providing a second engine by changing the first speed ratio of the first engine to a second speed ratio.
    Type: Grant
    Filed: September 10, 2019
    Date of Patent: February 14, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Ghislain Plante, Keith Morgan, Stephen Mah, Patrick Valois, Robert Peluso
  • Power cable cooling system in a gas turbine engine
    Patent number: 11578657
    Abstract: The cooling system may comprise: an electric machine; a first conduit including a cable housing and an inlet; a plurality of conductive cables extending from the electric machine, the plurality of conductive cables disposed at least partially in the cable housing; and an electric fan disposed in the first conduit, the cooling system configured to passively flow air through the first conduit to cool the plurality of conductive cables during operation of the gas turbine engine, and the electric fan configured to actively cool the plurality of conductive cables after an engine shutdown of the gas turbine engine.
    Type: Grant
    Filed: October 27, 2020
    Date of Patent: February 14, 2023
    Assignee: Raytheon Technologies Corporation
    Inventors: Marc J. Muldoon, Jonathan M. Rheaume
  • Combined heat and power system and method of operation
    Patent number: 11578652
    Abstract: A combined heat and power system and method of operation is provided. The system includes a combustion chamber configured to directly combust solid organic material. A compressor turbine is fluidly coupled to the combustion chamber. An expansion turbine is fluidly coupled to the combustion chamber. In an embodiment, the system has a low turbine pressure ratio.
    Type: Grant
    Filed: August 12, 2019
    Date of Patent: February 14, 2023
    Assignee: ENEXOR ENERGY, LLC
    Inventor: Ricardo Conde
  • Method for propelling an aircraft, propulsion system, and aircraft
    Patent number: 11572190
    Abstract: In the method for propelling an aircraft, to obtain electric energy, a fuel is combusted, and an electric machine is used, wherein the fuel is used to cool at least one part of the electric machine and contains natural gas. The propulsion system is configured to propel an aircraft, in particular according to the above-mentioned method. The propulsion system has an electric machine configured to obtain electric energy by combusting a fuel. The propulsion system further includes a natural gas tank configured to supply the fuel formed with natural gas, and a cooling device configured to cool at least one part of the electric machine. The aircraft has such a propulsion system.
    Type: Grant
    Filed: September 27, 2018
    Date of Patent: February 7, 2023
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Stefan Moldenhauer
  • Aircraft engine assembly with a supply path to an inter-flow compartment tank of turbine engine
    Patent number: 11572833
    Abstract: An aircraft engine assembly includes a dual-flow turbine engine, a pylon for mounting the turbine engine, thrust-absorbing rods connecting the turbine engine to the pylon, and an inter-flow compartment housing a lubricant tank. In order to facilitate the filling of the tank, a lubricant supply path is fluidly connected to the tank, this path passing through an inner hollow region of at least one of the two thrust-absorbing rods.
    Type: Grant
    Filed: April 2, 2019
    Date of Patent: February 7, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Antoine Elie Hellegouarch, Frédéric Paul Eichstadt, Quentin Matthias Emmanuel Garnaud
  • Multi-mode combustion control for a rotating detonation combustion system
    Patent number: 11572840
    Abstract: A computer-implemented method for multi-mode operation of a combustion system, a combustion system, and a heat engine are provided. The method includes initializing combustion of a fuel/oxidizer mixture, determining whether conditions at the combustion system meet or exceed a first threshold operating parameter, transitioning to detonation combustion of the fuel/oxidizer mixture if conditions at the combustion system meet or exceed the first threshold operating parameter, and maintaining or increasing fuel flow through a deflagrative fuel circuit if conditions at the combustion system do not meet or exceed the first threshold operating parameter.
    Type: Grant
    Filed: December 3, 2019
    Date of Patent: February 7, 2023
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Joel Meier Haynes, Sarah Marie Monahan, Thomas Michael Lavertu, Venkat Eswarlu Tangirala, Kapil Kumar Singh