Having Fuel Supply System Patents (Class 60/734)
  • Patent number: 12241415
    Abstract: A method of operating a gas turbine engine includes an engine core with a turbine, compressor, fuel combustor, and core shaft; a fan upstream of the engine core; a gearbox that receives an input from the core shaft and outputs drive to the fan; an oil loop system supplying oil to the gearbox; and a heat exchange system including: air-oil and fuel-oil heat exchangers, and wherein the oil loop system branches such that part of the oil flows along each branch and the air-oil and fuel-oil heat exchangers are parallel on different branches; and a modulation valve allows the oil sent via each branch to be varied, the method including controlling the heat exchange system wherein, under cruise conditions, a heat transfer ratio of: rate ? of ? heat ? transfer ? from ? oil ? to ? air rate ? of ? heat ? transfer ? from ? oil ? to ? fuel is in the range from 0 to 0.67.
    Type: Grant
    Filed: June 25, 2024
    Date of Patent: March 4, 2025
    Assignee: ROLLS-ROYCE plc
    Inventors: Benjamin J Keeler, Craig W Bemment, Andrea Minelli, Alastair G Hobday, Andrew T Smith
  • Patent number: 12227166
    Abstract: An example method of managing power in a hybrid propulsion system includes receiving, by one or more processors, a power demand that specifies an amount of power to be used to propel a vehicle that includes an electrical energy storage system (ESS) and one or more electrical generators, wherein the one or more electrical generators are configured to convert mechanical energy to electrical energy; determining, based on the power demand and a predetermined ESS output limit, a first amount of power to be sourced from the ESS and a second amount of power to be sourced from the one or more generators; and causing, by the one or more processors, the ESS to output the first amount of power onto a direct current (DC) electrical distribution bus and the one or more generators to output the second amount of power onto the DC electrical distribution bus.
    Type: Grant
    Filed: April 14, 2021
    Date of Patent: February 18, 2025
    Assignee: Rolls-Royce Corporation
    Inventor: Michael P. Dougherty
  • Patent number: 12228070
    Abstract: A reconfigurable hybrid solar gas turbine system includes a turbocharger (TC), a gas turbine engine, and a solar energy module. The TC and engine each include a compressor and a turbine joined by a turboshaft. The engine further includes a burner, a mixer, a generator, and a flow control valve. The system operates in a semi-open cycle in which the TC receives inlet ambient air. The burner receives pressurized air from the TC and fuel, for example from an NG source. The mixer combines hot gas flows from both the burner and the solar energy module to form a combined flow, whose mixing ratio is determined by a position of the flow control valve, thereby reconfiguring the system in response to variations in incident solar irradiance. Electrical power is generated by the engine generator and an optional TC generator. The engine and/or solar energy module may include a recuperator.
    Type: Grant
    Filed: May 25, 2021
    Date of Patent: February 18, 2025
    Assignee: TURBOGEN LTD.
    Inventor: David Lior
  • Patent number: 12180895
    Abstract: Methods and systems of operating a gas turbine engine in a low-power condition are provided. In one embodiment, the method includes supplying fuel to a combustor by supplying fuel to a first fuel manifold and a second fuel manifold of the gas turbine engine. The method also includes, while supplying fuel to the combustor by supplying fuel to the first fuel manifold: stopping supplying fuel to the second fuel manifold; and supplying pressurized air to the second fuel manifold to flush fuel in the second fuel manifold into the combustor and hinder coking in the second fuel manifold and associated fuel nozzles.
    Type: Grant
    Filed: June 30, 2023
    Date of Patent: December 31, 2024
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: James Robert Jarvo, Cedric Saintignan, Joseph Daniel Maxim Cirtwill, Kian McCaldon, Marc-Andre Tremblay, David Waddleton
  • Patent number: 12176793
    Abstract: The invention relates to a method for regulating an acceleration of a turbomachine, the turbomachine comprising a combustion chamber, a high-pressure turbine located downstream of the combustion chamber and which drives a high-pressure shaft in rotation, and a low-pressure turbine located downstream of the high-pressure turbine and which drives a low-pressure shaft in rotation, characterized in that the method comprises the following steps: injecting mechanical power onto the high-pressure shaft until a speed of the high-pressure shaft attains a target value, then extracting mechanical power from the high-pressure shaft so as to maintain the speed at the target value.
    Type: Grant
    Filed: April 27, 2020
    Date of Patent: December 24, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Romain Guillaume Cuvillier, Pierre Cabrera
  • Patent number: 12146478
    Abstract: A fuel pump system includes a main fuel pump between a system fuel inlet and a system fuel outlet, a fuel flow path at least partially defined between the main fuel pump and the system fuel outlet, and a support fuel pump between the system fuel inlet and the system fuel outlet. The support fuel pump is sized to provide more flow to the system fuel outlet, when in an active state, than the main fuel pump. The system includes a valve assembly in fluid communication with the support fuel pump configured and adapted to connect the support fuel pump to the system fuel outlet, and a pressure regulating valve in fluid communication with the fuel flow path between the main fuel pump and the system fuel outlet. The system includes an EHSV in fluid communication with the fuel flow path between the PRV and the system fuel outlet.
    Type: Grant
    Filed: May 26, 2022
    Date of Patent: November 19, 2024
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Morgan O′Rorke, Ryan Susca, Ryan Shook
  • Patent number: 12110827
    Abstract: A turbo engine for an aircraft includes a gas turbine engine having a combustion section and a fuel system to provide pressurized fuel to the combustion section. The fuel system includes a fuel tank and a boost pump and a main pump driven by an accessory gearbox that is powered by a shaft of the turbo engine. The boost pump and the main pump are arranged in series. The fuel system also includes an auxiliary pump and a controller to operate the fuel system in (1) a first mode in which the boost pump and the main pump produce pressurized fuel for the turbo engine and the auxiliary pump is deactivated, and (2) a second mode in which the auxiliary pump is activated and produces the pressurized fuel for the turbo engine while bypassing the boost pump and the main pump.
    Type: Grant
    Filed: May 3, 2023
    Date of Patent: October 8, 2024
    Assignee: General Electric Company
    Inventors: Jeffrey D. Rambo, Scott G. Edens, Michael Joseph Murray
  • Patent number: 12071899
    Abstract: A pump system for a gas turbine engine including a first pump connected to a fluid flow demand line for delivering fluid to a fluid flow demand and a second pump connected, in parallel to the first pump, to the fluid flow demand line and supplementing fluid to the actuation or burner system based on the fluid flow demand. A pressure regulating valve (PRV) is fluidly connected to the flow demand line for bypassing flow to a pump inlet pressure of the first pump and second pump, and controlling a modulated pressure flow signal to a bypass valve, wherein the bypass valve is in fluid communication with the second pump and the PRV for receiving modulated pressure from the PRV and regulating delivery of fluid from the second pump to a bypass flow line.
    Type: Grant
    Filed: May 15, 2023
    Date of Patent: August 27, 2024
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Todd Haugsjaahabink, Ryan Shook
  • Patent number: 12065978
    Abstract: A control method is provided for an engine. During this control method, a lambda target parameter indicative of a ratio between a stoichiometric air-to-fuel ratio and an actual air-to-fuel ratio is determined. A control signal is determined using the lambda target parameter. A component of the engine is operated based on the control signal to regulate airflow within a compressor section of the engine.
    Type: Grant
    Filed: November 1, 2022
    Date of Patent: August 20, 2024
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Etienne Plamondon
  • Patent number: 12060831
    Abstract: A system includes a plurality of injectors each having a respective main circuit configured to be connected in fluid communication with one manifold for supplying fuel to each injector in the plurality of injectors. Each injector in the plurality of injectors includes a respective hydromechanical scheduling valve member configured to regulate fuel flow from a respective inlet to a respective nozzle of each injector of the plurality of injectors as a function of pressure input from the manifold to the respective main circuits. A valve block is connected in fluid communication with a respective auxiliary circuit in each injector in the plurality of injectors. The auxiliary circuit is operatively connected to adjust position of the respective scheduling valve member for actuating force modification of the scheduling valve member. The valve block is configured to control all of the injectors in the plurality of injectors as a block.
    Type: Grant
    Filed: September 11, 2023
    Date of Patent: August 13, 2024
    Assignee: Collins Engine Nozzles, Inc.
    Inventors: Brandon P. Williams, Michael Ferrarotti, Murtuza Lokhandwalla, Todd Haugsjaahabink, Russell P. Rourke, Jr., Jay W. Kokas, Richard E. Versailles
  • Patent number: 12055099
    Abstract: A two stage fuel delivery system for an aircraft includes a first stage pump including an inlet connected to a source of fuel and an outlet connected to a combustor assembly, and a second stage pump including an inlet portion connected to the source of fuel and an outlet portion connected to the combustor assembly. A bypass valve is connected between the source of fuel, the inlet, and the inlet portion. The bypass valve selectively disconnects the second stage pump from the source of fuel. A metering valve is connected to the inlet and the inlet portion. The metering valve includes a metering valve inlet and a metering valve outlet. A pressure regulating valve is connected to the metering valve. A stage monitoring system is configured to detect a change in operation of the second stage and control the bypass valve.
    Type: Grant
    Filed: July 19, 2022
    Date of Patent: August 6, 2024
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Ryan Prescott Susca, Todd Haugsjaahabink, Naison E. Mastrocola, Adrian L. Stoicescu, Zachary Allen Ray LeDuc, Eric Briggs, Morgan O'Rorke
  • Patent number: 12030667
    Abstract: A flow booster for optimizing flow of fuel passing into an aircraft. The flow booster includes a fuel intake fluidly coupled to the fuel circuit, and includes a housing and a piston. The piston has a piston head slidably movable in the housing to define h a variable fuel inlet to receive the fuel. The fuel applies a fuel force to the piston. An intake tuner is operatively connected to the fuel M intake, and has a tuning force applied to the piston against the fuel force. A trigger is coupled to the intake tuner to vary the tuning force applied by the intake tuner. The flow regulator is coupled to sensors to receive fuel measurements. A flow regulator is operatively connected to the trigger to activate the trigger in response to the fuel measurements whereby the flow of the fuel into the aircraft is continuously adjustable during refueling.
    Type: Grant
    Filed: January 8, 2019
    Date of Patent: July 9, 2024
    Assignee: SHELL USA, INC.
    Inventors: Bernhard Hans Maedler, Griffin Michael Valentich
  • Patent number: 12012233
    Abstract: Chemical propellant storage and supply systems and methods for use on spacecraft are provided. The systems and methods include a fluid pump for moving chemical propellant within the system at selected pressures. This can include operating the fluid pump to supply propellant to a thruster system at a selected pressure. A fuel tank can be refilled by connecting a propellant resupply source to the system, and operating the fluid pump to move propellant from the propellant resupply source to the fuel tank. In a system with multiple fuel tanks, the fluid pump can be operated to move propellant from a donor fuel tank to a recipient fuel tank. The chemical propellant can be stored in one or more fuel tanks at a relatively low pressure. In addition, the chemical propellant is not pressurized by a gaseous pressurant while it is stored in the fuel tank.
    Type: Grant
    Filed: May 9, 2022
    Date of Patent: June 18, 2024
    Assignee: Ball Aerospace & Technologies Corp.
    Inventors: Gordon C. Wu, Derek Chan, Robert J. Baltrum, Jr., Eric R. Turner
  • Patent number: 12012905
    Abstract: A control device selects and executes any of normal control of outputting a fuel flow rate command value through feedback control based on a deviation between a target output and an actual output of a gas turbine and load decreasing control of outputting the fuel flow rate command value for reducing an output of the gas turbine to a predetermined target output during a predetermined first time without performing feedback control, and performs control of reducing a flow rate of air flowing into a compressor of the gas turbine such that an air-fuel ratio settles within a predetermined range, in parallel with execution of the load decreasing control when the load decreasing control is selected.
    Type: Grant
    Filed: November 30, 2018
    Date of Patent: June 18, 2024
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Keisuke Yamamoto, Kazushige Takaki, Makoto Kishi, Shinya Uchida, Hisashi Nakahara, Hikaru Katano, Yoshikazu Ui
  • Patent number: 11970977
    Abstract: A fuel injector for a turbine engine includes a fuel scheduling valve configured for regulation of fuel flow from a fuel inlet, in response to fuel pressure received at the fuel inlet. Primary, secondary and auxiliary fuel circuits receive fuel from the scheduling valve, and an electrically-controlled valve is provided in fluid communication with the auxiliary circuit, which electrically-controlled valve is adapted and configured to actively control fuel through the auxiliary circuit in response to a control signal. The auxiliary fuel circuit joins with the secondary fuel circuit for delivery to a fuel nozzle.
    Type: Grant
    Filed: August 26, 2022
    Date of Patent: April 30, 2024
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Murtuza Lokhandwalla, Brandon P. Williams, Jason A. Ryon, Todd Haugsjaahabink
  • Patent number: 11970976
    Abstract: A fuel injector for a turbine engine includes a fuel scheduling valve configured for regulation of fuel flow from a fuel inlet, in response to fuel pressure received at the fuel inlet. Primary, secondary and auxiliary fuel circuits receive fuel from the scheduling valve, and an electrically-controlled valve is provided in fluid communication with the auxiliary circuit, which electrically-controlled valve is adapted and configured to actively control fuel through the auxiliary circuit in response to a control signal.
    Type: Grant
    Filed: August 26, 2022
    Date of Patent: April 30, 2024
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Murtuza Lokhandwalla, Brandon P. Williams, Todd Haugsjaahabink, Charles E. Reuter, Jason A. Ryon, Kevin Gibbons, Jesse C. Peters
  • Patent number: 11965424
    Abstract: A method for providing overspeed protection for a gas turbine engine having an engine shaft includes monitoring, via an overspeed protection system, a torque of the engine shaft. The method also includes determining, via the overspeed protection system, at least one additional condition of the engine shaft. Further, the method includes determining, via the overspeed protection system, an overspeed condition of the gas turbine engine when the torque of the engine shaft drops below a torque threshold and the at least one additional condition of the engine shaft is indicative of the gas turbine engine being in an operational state. Thus, the overspeed condition is indicative of an above normal rotational speed of the engine shaft. In addition, the method includes initiating a shutdown procedure for the gas turbine engine in response to the determined overspeed condition to reduce the rotational speed of the engine shaft.
    Type: Grant
    Filed: June 21, 2022
    Date of Patent: April 23, 2024
    Assignee: General Electric Company
    Inventors: Arthur William Sibbach, Brandon Wayne Miller, Erich Alois Krammer, Douglas Scott Jacobs, Joseph Alfred Iannotti
  • Patent number: 11905898
    Abstract: A method of automated timing of engine startup for an aircraft is provided. The method comprises receiving data inputs regarding a number of factors influencing a time to departure for the aircraft and receiving data inputs regarding a number of factors influencing time to start and set takeoff power for a number of engines on the aircraft. An engine startup countdown is calculated based on a comparison of a nominal time to departure with a nominal minimum time to start and set takeoff power for the engines, wherein the nominal time to departure is based on the first data inputs and the nominal minimum time to start and set takeoff power is based on the second data inputs. Upon completion of the countdown an engine start signal is sent.
    Type: Grant
    Filed: December 19, 2019
    Date of Patent: February 20, 2024
    Assignee: The Boeing Company
    Inventors: Jeffrey S. Siegmeth, David William Foutch, Bruce Van Deventer
  • Patent number: 11891971
    Abstract: In a droplet ejector equipped with an ejection port for ejecting minute droplets of a liquid, the ejection port 61 or the ejector and a conductor 10 such as a vehicle body are made electrically conductive to increase the electrostatic capacity of the ejection port 61 or the ejector and to suppress enlargement of the potential difference between the ejection port 61 and the liquid caused by flow electrification of the liquid. When the potential difference is large, a coulomb force acts between the electrified droplets and the electrostatically-charged ejection port, causing problems such as delayed or insufficient droplet discharge, but such problems are solved by increasing the electrostatic capacity of the ejection port 61 or the ejector.
    Type: Grant
    Filed: December 26, 2019
    Date of Patent: February 6, 2024
    Inventors: Fuminori Saito, Tokihiro Ikeda
  • Patent number: 11879384
    Abstract: Methods and systems of starting a gas turbine engine are provided. During startup, a fuel pressure associated with a primary fuel supply of the gas turbine engine is monitored. A low-pressure event for the primary fuel supply is detected when the fuel pressure falls below a predetermined threshold. Responsive to detecting the low pressure event, an electric backup boost pump is activated by an engine controller to provide fuel to the gas turbine engine.
    Type: Grant
    Filed: February 9, 2023
    Date of Patent: January 23, 2024
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Sean Durand
  • Patent number: 11867118
    Abstract: Methods and systems for supply of fuel for a turbine-driven fracturing pump system used in hydraulic fracturing may be configured to identify when the supply pressure of primary fuel to a plurality of gas turbine engines of a plurality of hydraulic fracturing units falls below a set point, identify a gas turbine engine of the fleet of hydraulic fracturing units operating on primary fuel with highest amount of secondary fuel available, and to selectively transfer the gas turbine engine operating on primary fuel with the highest amount of secondary fuel from primary fuel operation to secondary fuel operation. Some methods and systems may be configured to transfer all gas turbine engines to secondary fuel operation and individually and/or sequentially restore operation to primary fuel operation and/or to manage primary fuel operation and/or secondary fuel operation for portions of the plurality of gas turbine engines.
    Type: Grant
    Filed: February 24, 2023
    Date of Patent: January 9, 2024
    Assignee: BJ Energy Solutions, LLC
    Inventors: Tony Yeung, Ricardo Rodriguez-Ramon, Joseph Foster
  • Patent number: 11859551
    Abstract: A fuel system can include a selection and shutoff valve (SSOV) configured to allow a primary flow having a primary flow pressure to pass therethrough in a first state such that the primary flow can travel to an output line. The SSOV can also be configured to shut off the primary flow in a second state to prevent the primary flow from travelling to the output line. In the second state, the SSOV can be configured to allow a secondary flow from a secondary flow source to pass therethrough such that the secondary flow can travel to the output line.
    Type: Grant
    Filed: January 21, 2022
    Date of Patent: January 2, 2024
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Morgan O'Rorke, Todd Haugsjaahabink, Matej Rutar, Ryan Susca
  • Patent number: 11828228
    Abstract: An aircraft includes a machine body that encloses a turbofan gas turbine engine and a plurality of ancillary systems. The turbofan gas turbine engine includes, in axial flow sequence, a first heat exchanger module, a fan assembly, a compressor module, a combustor module, a turbine module, and an exhaust module. The aircraft includes a second heat exchanger module. The machine body comprises a single fluid inlet aperture, with the fluid inlet aperture being configured to allow a fluid cooling flow to enter the machine body and to pass through the first heat exchanger module. When a temperature of the fluid cooling flow is less than a temperature of a fluid to be cooled, the fluid to be cooled is directed to the first heat exchanger module, and when a temperature of the fluid cooling flow is greater than a temperature of the fluid to be cooled, the fluid to be cooled is directed to the second heat exchanger module and cooled using a fuel supply for the gas turbine engine.
    Type: Grant
    Filed: February 16, 2023
    Date of Patent: November 28, 2023
    Assignee: ROLLS-ROYCE plc
    Inventors: Natalie C Wong, Thomas S Binnington, David A Jones, Daniel Blacker
  • Patent number: 11761382
    Abstract: A fuel supply device includes a first electric pump which discharges a fuel toward an engine at a first flow rate, a second electric pump which discharges the fuel at a second flow rate and merges the fuel discharged at the second flow rate with the fuel discharged at the first flow rate, a first control device which is configured to control the first electric pump, and a second control device which is configured to control the second electric pump, in which the first control device and the second control device control the first electric pump and the second electric pump such that a total flow rate of the first flow rate and the second flow rate is a fuel flow rate target value.
    Type: Grant
    Filed: June 5, 2020
    Date of Patent: September 19, 2023
    Assignee: IHI Corporation
    Inventor: Yasuhiko Yamamoto
  • Patent number: 11746704
    Abstract: A hydrogen content fuel can be stably ignited using a gaseous fuel that does not contain hydrogen and dispersibility of the hydrogen content fuel is enhanced. A gas turbine combustor including a burner including: a startup fuel pipe in which a startup fuel circulates; a first main fuel pipe in which a main fuel circulates, a second main fuel pipe in which the main fuel circulates; a fuel mixer to which the startup fuel pipe and the first main fuel pipe are connected; an inner fuel nozzle to which the fuel mixer is connected; a plurality of outer fuel nozzles to which the second main fuel pipe is connected; a startup fuel control valve provided in the startup fuel pipe; a first fuel control valve provided in the first main fuel pipe; and a second fuel control valve provided in the second main fuel pipe.
    Type: Grant
    Filed: September 29, 2020
    Date of Patent: September 5, 2023
    Assignee: Mitsubishi Heavy Industries, Ltd.
    Inventors: Tomohiro Asai, Shohei Yoshida, Yoshitaka Hirata, Akinori Hayashi, Yasuhiro Akiyama, Yoshinori Matsubara
  • Patent number: 11725585
    Abstract: In accordance with at least one aspect of this disclosure, a pump selector system can include a primary pump fluidly connected to provide a primary flow to a fluid destination, a secondary pump fluidly connected to provide a secondary flow to the fluid destination, and a selector valve disposed downstream of the primary pump and the secondary pump. The selector valve can be configured to toggle between a first position configured to allow flow from the primary pump to flow to the fluid destination and to block flow from the secondary pump to the fluid destination, and a second position configured to allow flow from the secondary pump to flow to the fluid destination and to block flow from the primary pump to the fluid destination.
    Type: Grant
    Filed: November 30, 2021
    Date of Patent: August 15, 2023
    Assignee: Hamilton Sundstrand Corporation (HSC)
    Inventors: Ryan Susca, Todd Haugsjaahabink, Morgan O'Rorke
  • Patent number: 11702990
    Abstract: A redundant oil and fuel pumping system for use with a gas turbine engine. The pumping system includes a plurality of power sources, a fuel system and an oil system. The fuel system pump being driven by electric motors controlled via variable frequency drives powered by the plurality of power sources. The oil system pump being driven by electric motors controlled via variable frequency drives powered by the plurality of power sources.
    Type: Grant
    Filed: September 8, 2021
    Date of Patent: July 18, 2023
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventor: Alan W. Smith
  • Patent number: 11674444
    Abstract: A system includes a flow inlet conduit and a primary conduit that branches from the flow inlet conduit for delivering flow to a set of primary nozzles. An equalization bypass valve (EBV) connects between the flow inlet conduit and a secondary conduit for delivering flow to a set of secondary nozzles. The EBV is connected to an equalization conduit (EC). A pressure equalization solenoid is connected to the EC to selectively connect a servo supply pressure conduit and/or a return pressure (PDF) conduit into fluid communication with the EC. An EBV rate limiting orifice (RLO) is connected in the PDF conduit. A bypass conduit branches from the PDF conduit on a first side of the EBV RLO and reconnects to the PDF conduit on a second side of the EBV RLO. An orifice bypass valve (OBV) is connected to the bypass conduit and acts to selectively bypass the EBV RLO.
    Type: Grant
    Filed: March 30, 2021
    Date of Patent: June 13, 2023
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Charles E. Reuter, Aaron F. Rickis, Francis P. Marocchini, Matej Rutar, August M. Coretto, Sachin Ramprashad
  • Patent number: 11649768
    Abstract: A pump system for a gas turbine engine including a first pump connected to a fluid flow demand line for delivering fluid to a fluid flow demand and a second pump connected, in parallel to the first pump, to the fluid flow demand line and supplementing fluid to the actuation or burner system based on the fluid flow demand. A pressure regulating valve (PRV) is fluidly connected to the flow demand line for bypassing flow to a pump inlet pressure of the first pump and second pump, and controlling a modulated pressure flow signal to a bypass valve, wherein the bypass valve is in fluid communication with the second pump and the PRV for receiving modulated pressure from the PRV and regulating delivery of fluid from the second pump to a bypass flow line.
    Type: Grant
    Filed: August 20, 2021
    Date of Patent: May 16, 2023
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Todd Haugsjaahabink, Ryan Shook
  • Patent number: 11629717
    Abstract: Apparatus and associated methods relate to simultaneously pumping and measuring density of an aircraft fuel. The aircraft fuel is pumped by a centrifugal pump having an impeller. A rotational frequency of the impeller is determined while the centrifugal pump is pumping the aircraft fuel. Flow rate of the aircraft fuel through the centrifugal pump is sensed. Pressure of the aircraft fuel is measured at two different points within or across the centrifugal pump or a differential pressure is measured between the two different points while the centrifugal pump is pumping the aircraft fuel. Density of the aircraft fuel is determined based on an empirically-determined head-curve relation corresponding to the centrifugal pump. The head-curve relation is empirically determined during a characterization phase. The empirically-determined head-curve relation relates the density of the aircraft fuel to the rotational frequency, the flow rate, and the pressures at the two different points.
    Type: Grant
    Filed: November 8, 2019
    Date of Patent: April 18, 2023
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Charles E. Reuter, Gerald P. Dyer
  • Patent number: 11629643
    Abstract: A fuel pump system, comprising an inlet line and a motorized pump, a first selector valve in fluid communication with an inlet line at a first inlet port and in fluid communication with the motorized pump outlet via a first outlet branch at a second inlet port to receive fuel from the motorized pump outlet. The system can also include a main fuel pump in fluid communication with the first selector valve and a second selector valve, wherein the second selector valve can be in fluid communication with the main fuel pump and in fluid communication with the motorized pump outlet.
    Type: Grant
    Filed: January 7, 2022
    Date of Patent: April 18, 2023
    Assignee: Hamilton Sundstrand Corporation
    Inventor: Ryan Susca
  • Patent number: 11499559
    Abstract: A fluid pump includes a housing; an inlet passage; an outlet conduit; a pumping element within the housing; and a check valve assembly. The check valve assembly includes a valve stem within the outlet conduit such that a flow path is created radially between the outlet conduit and the valve stem, the valve stem moving along a check valve assembly axis between a closed position and an open position. The flow path includes a first restriction which increases velocity of fluid passing through the flow path; a first expansion, downstream of the first restriction, which decreases velocity of fluid passing through the flow path; a second restriction, downstream of the first expansion, which increases velocity of fluid passing through the flow path; and a second expansion, downstream of the second restriction, which decreases velocity of fluid passing through the flow path.
    Type: Grant
    Filed: October 30, 2020
    Date of Patent: November 15, 2022
    Assignee: DELPHI TECHNOLOGIES IP LIMITED
    Inventors: Francisco Romo, Sonia Espinoza
  • Patent number: 11466626
    Abstract: A method for controlling a turbomachine comprising an electric motor forming a torque injection device on a high-pressure rotation shaft, in which method a fuel flow setpoint QCMD and a torque setpoint TRQCMD provided at the electric motor are determined, the control method comprising: • a step of implementing a first fuel control loop in order to determine the fuel flow set point QCMD, • a step of implementing a second, torque control loop in order to determine the torque setpoint TRQCMD comprising i. a step of determining a torque correction variable ?TRQCMD as a function of a transitory speed setpoint NHTrajAccelCons, NHTrajDecelCons and ii. a step of determining the torque setpoint TRQCMD as a function of the torque correction variable ?TRQCMD.
    Type: Grant
    Filed: October 1, 2019
    Date of Patent: October 11, 2022
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventor: Cedrik Djelassi
  • Patent number: 11391645
    Abstract: Certain aspects of the present disclosure generally relate to an optical reference element having a wavelength spectrum comprising a plurality of wavelength functions having wavelength peaks spaced over a range of wavelengths, wherein adjacent wavelength functions are due to two orthogonal birefringence axes in the optical reference element. Aspects of the present disclosure may eliminate the drift issues associated with residual polarization and polarization dependent loss (PDL) with respect to grating-based sensor and reference element measurements.
    Type: Grant
    Filed: February 5, 2019
    Date of Patent: July 19, 2022
    Assignee: Weatherford Technology Holdings, LLC
    Inventor: Domino Taverner
  • Patent number: 11346239
    Abstract: A method of measuring a gas turbine engine component of a gas turbine engine according to an example of the present disclosure includes, among other things, providing at least one gas turbine engine component including a coating on a substrate, detecting infrared radiation emitted from at least one localized region of the coating at a first wavelength in a first electromagnetic radiation frequency range, detecting infrared radiation emitted from the substrate corresponding to the at least one localized region at a second, different wavelength in a second electromagnetic radiation frequency range that differs from the first electromagnetic radiation frequency range, and determining a heat flux relating to the at least one localized region based upon a comparison of the first wavelength and the second wavelength.
    Type: Grant
    Filed: September 18, 2020
    Date of Patent: May 31, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Shayan Ahmadian, Charles W. Haldeman, Mark F. Zelesky, Christopher T. Bergman, Sebastian Martinez
  • Patent number: 11230979
    Abstract: A liquid fuel system for an aircraft engine includes a first fuel supply conduit hydraulically connected to a fuel source, a second fuel supply conduit hydraulically connected to the engine, a fuel return conduit hydraulically connected to the second fuel supply conduit, and a fuel pump. The fuel pump has a main inlet hydraulically connected to the first fuel supply conduit, an outlet hydraulically connected to the second fuel supply conduit, and an intermediate inlet hydraulically connected to the fuel return conduit. The intermediate inlet is located between the main inlet and the outlet and in use has a pressure between the main inlet pressure and the outlet pressure. A method of supplying a liquid fuel to an aircraft engine is also described.
    Type: Grant
    Filed: March 8, 2019
    Date of Patent: January 25, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: David Waddleton, Benjamin Renaud, Sebastien Bergeron, Etienne Plamondon, Jean-Gabriel Gauvreau
  • Patent number: 11191294
    Abstract: Apparatus and methods for making puffed food products are disclosed. In one implementation, an innovative process may include improved configurations and control of hydraulic drive cylinder(s) to more swiftly and precisely apply pressures to heatable mold elements during production of puffed food products. According to one particular implementation, in order to drive a first hydraulic piston to move at least one movable mold element to a desired position, a second hydraulic piston may be first positioned to set up an adjustable hard-stop based on the desired position, such that the first hydraulic piston may rapidly drive the moveable mold element to stop at precisely the desired position.
    Type: Grant
    Filed: July 26, 2019
    Date of Patent: December 7, 2021
    Assignee: Ideal Snacks Corporation
    Inventor: Steven Van Poucke
  • Patent number: 11187154
    Abstract: The subject matter of this specification can be embodied in, among other things, a fuel delivery component, a substantially rigid, unitary structure formed as a single piece of material, and at least a first seamless lumen defined by the unitary structure as a first loop.
    Type: Grant
    Filed: March 13, 2019
    Date of Patent: November 30, 2021
    Assignee: Woodward, Inc.
    Inventors: Mark Allen Broome, Seth E. Rutan, Mark G. Goeddeke
  • Patent number: 11187153
    Abstract: The subject matter of this specification can be embodied in, among other things, a fuel delivery component, including a substantially rigid, unitary structure formed as a single piece of material, and at least a first seamless lumen defined by the unitary structure.
    Type: Grant
    Filed: March 13, 2019
    Date of Patent: November 30, 2021
    Assignee: Woodward, Inc.
    Inventors: Mark Allen Broome, Seth E. Rutan, Mark G. Goeddeke
  • Patent number: 11085375
    Abstract: A combustor assembly for a gas turbine engine includes a plurality of combustors spaced circumferentially about the gas turbine engine. Each of the combustors is coupled in flow communication with a manifold configured to channel a liquid to the plurality of combustors. A plurality of fuel lines is coupled in flow communication with the manifold. Each fuel line is coupled in flow communication with a respective combustor of the plurality of combustors. In addition, the combustor assembly includes a flow balance system having a plurality of flow balance devices. Each flow balance device is operatively coupled to one of the fuel lines. Each flow balance device is operative to reduce the flow of liquid to the respective combustor.
    Type: Grant
    Filed: June 15, 2017
    Date of Patent: August 10, 2021
    Assignee: General Electric Company
    Inventors: Kihyung Kim, Anthony Whittenberg
  • Patent number: 11067278
    Abstract: A fuel system includes a fuel supply system. A plurality of fuel nozzles are connected in fluid communication with the fuel supply system to supply fuel from a fuel source to be issued for combustion from the fuel nozzles. A cooling system is included, wherein at least one of the fuel nozzles includes a cooling circuit in addition to a fuel circuit for issuing fuel from the fuel supply system for combustion. The cooling circuit includes an inlet and an outlet. The inlet is in fluid communication with the cooling system for circulation of coolant through the cooling circuit and back to the cooling system out the outlet of the cooling circuit for cooling the fuel circuit with the fuel circuit staged off.
    Type: Grant
    Filed: May 30, 2018
    Date of Patent: July 20, 2021
    Assignee: Delavan Inc.
    Inventors: Lev Alexander Prociw, Timothy Griffith
  • Patent number: 10989118
    Abstract: Provided are turbine engines and methods of operating thereof by heating and evaporating liquid fuels in a controlled manner prior to burning. Specifically, a fuel is heated and evaporated while avoiding coking. Coking is caused by pyrolysis when the fuel contacts a metal surface within a certain temperature range, which is referred herein to a coking temperature range. In the described methods, the fuel is transferred from one component, maintained below the coking temperature range, to another component, maintained above this range. The fuel is airborne and does not contact any metal surfaces during this transfer, and coking does not occur. In some examples, the fuel is also mixed with hot air during this transfer. The heated fuel, e.g., as an air-fuel mixture, is then supplied into a combustor, where more air is added to reach flammability conditions.
    Type: Grant
    Filed: December 20, 2018
    Date of Patent: April 27, 2021
    Assignee: WRIGHTSPEED, INC.
    Inventors: Ian Wright, Brandon Stitt
  • Patent number: 10975805
    Abstract: An engine start system includes a facility that has a ground based hydraulic pressurization system and a combustor of a liquid propellant rocket engine. The engine is fluidly coupled to the ground based hydraulic pressurization system. The liquid propellant rocket engine is operably detachable from the ground based hydraulic pressurization system.
    Type: Grant
    Filed: July 11, 2017
    Date of Patent: April 13, 2021
    Assignee: AEROJET ROCKETDYNE, INC.
    Inventors: Douglas Parker, Frederick Dodd
  • Patent number: 10801866
    Abstract: A measuring device for measuring a physical property of a fluid, including a base body which is closed along a peripheral line. The base body surrounds a first recess passing through the base body in the axial direction and the base body includes at least one second recess passing through the base body in the axial direction recess. At least one sensor device, which can be associated with the base body, can be bought into contact with the first recess.
    Type: Grant
    Filed: March 21, 2017
    Date of Patent: October 13, 2020
    Assignee: MTU FRIEDRICHSHAFEN GMBH
    Inventors: Ludwig Kläser-Jenewein, Ulrich Meyer
  • Patent number: 10598374
    Abstract: A method of inducing swirl in pressurized air flowing through an air passageway of a fuel nozzle of a gas turbine engine includes inducing swirl in the pressurized air at an exit of the air passageway, by directing the pressurised air through helicoidal grooves formed at a downstream end of the air passageway. The swirling pressurized air exiting the air passageway is then directed into a mixing zone at a downstream end of the fuel nozzle.
    Type: Grant
    Filed: August 3, 2017
    Date of Patent: March 24, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Yen-Wen Wang, Nigel Davenport
  • Patent number: 10428816
    Abstract: A multi-stage gear pump includes a first pump stage, a second pump stage, and a variable speed gearbox including an input and an output, wherein the input is rotationally coupled to the first pump stage and the input rotates at a first rotational speed, and the output is rotationally coupled to the second pump stage and rotates at a second rotational speed, wherein a variable gear ratio determines the second rotational speed relative to the first rotational speed.
    Type: Grant
    Filed: October 24, 2016
    Date of Patent: October 1, 2019
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventor: William E. Rhoden
  • Patent number: 10393281
    Abstract: A pressure relief system is provided and a corresponding method for relieving pressure from a duct routing a gas from a compressor to a load utilizing the same. According to one aspect, a pressure relief assembly, located near the load, and independent of the primary load compressor pressure relief valve, for use with a duct includes a cover, first and second chambers, and a piston. The piston provides a moveable wall between the chambers and is coupled to the cover. As gas from the duct enters the two chambers, the configuration of the chambers provides for a pressure differential that moves the piston and the corresponding cover. This movement transitions the cover from a closed configuration that seals the duct to an open configuration that allows gas within the duct to escape.
    Type: Grant
    Filed: October 25, 2016
    Date of Patent: August 27, 2019
    Assignee: The Boeing Company
    Inventors: Marcus Karel Richardson, David M. Smith
  • Patent number: 10190774
    Abstract: A fuel nozzle apparatus for a gas turbine engine includes: a fuel discharge element having a discharge orifice communicating with a fuel supply connection; a static supporting structure; and a cantilevered flexible support structure interconnecting the supporting structure and the fuel discharge element, the flexible support structure having a first end connected to the static supporting structure, and a second end connected to the fuel discharge element.
    Type: Grant
    Filed: December 23, 2014
    Date of Patent: January 29, 2019
    Assignee: General Electric Company
    Inventors: Joshua Tyler Mook, Jason Joseph Bellardi, Ting-Yu Tu
  • Patent number: 9920932
    Abstract: A mixer assembly for a gas turbine engine is provided, including a main mixer with fuel injection holes located between at least one radial swirler and at least one axial swirler, wherein the fuel injected into the main mixer is atomized and dispersed by the air flowing through the radial swirler and the axial swirler.
    Type: Grant
    Filed: January 9, 2015
    Date of Patent: March 20, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Zhongtao Dai, Jeffrey M. Cohen, Catalin G. Fotache, Lance L. Smith, Donald J. Hautman
  • Patent number: 9885355
    Abstract: A pump apparatus includes a shaft, a first pump, and a second pump. The first pump includes a first driving gear disposed on the shaft in a first phase and rotatable with the shaft to feed a first operating fluid. The second pump includes a second driving gear disposed on the shaft in a second phase shifted from the first phase. The second driving gear is coaxial with the first driving gear and rotatable with the shaft to feed a second operating fluid.
    Type: Grant
    Filed: September 25, 2015
    Date of Patent: February 6, 2018
    Assignee: SHOWA CORPORATION
    Inventors: Takahiko Saito, Atsushi Kagawa, Hayato Tsutsui