Having Fuel Supply System Patents (Class 60/734)
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Patent number: 12241415Abstract: 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: GrantFiled: June 25, 2024Date of Patent: March 4, 2025Assignee: ROLLS-ROYCE plcInventors: Benjamin J Keeler, Craig W Bemment, Andrea Minelli, Alastair G Hobday, Andrew T Smith
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Patent number: 12227166Abstract: 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: GrantFiled: April 14, 2021Date of Patent: February 18, 2025Assignee: Rolls-Royce CorporationInventor: Michael P. Dougherty
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Patent number: 12228070Abstract: 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: GrantFiled: May 25, 2021Date of Patent: February 18, 2025Assignee: TURBOGEN LTD.Inventor: David Lior
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Patent number: 12180895Abstract: 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: GrantFiled: June 30, 2023Date of Patent: December 31, 2024Assignee: PRATT & WHITNEY CANADA CORP.Inventors: James Robert Jarvo, Cedric Saintignan, Joseph Daniel Maxim Cirtwill, Kian McCaldon, Marc-Andre Tremblay, David Waddleton
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Patent number: 12176793Abstract: 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: GrantFiled: April 27, 2020Date of Patent: December 24, 2024Assignee: SAFRAN AIRCRAFT ENGINESInventors: Romain Guillaume Cuvillier, Pierre Cabrera
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Patent number: 12146478Abstract: 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: GrantFiled: May 26, 2022Date of Patent: November 19, 2024Assignee: Hamilton Sundstrand CorporationInventors: Morgan O′Rorke, Ryan Susca, Ryan Shook
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Patent number: 12110827Abstract: 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: GrantFiled: May 3, 2023Date of Patent: October 8, 2024Assignee: General Electric CompanyInventors: Jeffrey D. Rambo, Scott G. Edens, Michael Joseph Murray
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Patent number: 12071899Abstract: 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: GrantFiled: May 15, 2023Date of Patent: August 27, 2024Assignee: HAMILTON SUNDSTRAND CORPORATIONInventors: Todd Haugsjaahabink, Ryan Shook
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Patent number: 12065978Abstract: 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: GrantFiled: November 1, 2022Date of Patent: August 20, 2024Assignee: PRATT & WHITNEY CANADA CORP.Inventor: Etienne Plamondon
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Patent number: 12060831Abstract: 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: GrantFiled: September 11, 2023Date of Patent: August 13, 2024Assignee: Collins Engine Nozzles, Inc.Inventors: Brandon P. Williams, Michael Ferrarotti, Murtuza Lokhandwalla, Todd Haugsjaahabink, Russell P. Rourke, Jr., Jay W. Kokas, Richard E. Versailles
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Patent number: 12055099Abstract: 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: GrantFiled: July 19, 2022Date of Patent: August 6, 2024Assignee: HAMILTON SUNDSTRAND CORPORATIONInventors: Ryan Prescott Susca, Todd Haugsjaahabink, Naison E. Mastrocola, Adrian L. Stoicescu, Zachary Allen Ray LeDuc, Eric Briggs, Morgan O'Rorke
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Patent number: 12030667Abstract: 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: GrantFiled: January 8, 2019Date of Patent: July 9, 2024Assignee: SHELL USA, INC.Inventors: Bernhard Hans Maedler, Griffin Michael Valentich
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Patent number: 12012233Abstract: 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: GrantFiled: May 9, 2022Date of Patent: June 18, 2024Assignee: Ball Aerospace & Technologies Corp.Inventors: Gordon C. Wu, Derek Chan, Robert J. Baltrum, Jr., Eric R. Turner
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Patent number: 12012905Abstract: 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: GrantFiled: November 30, 2018Date of Patent: June 18, 2024Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.Inventors: Keisuke Yamamoto, Kazushige Takaki, Makoto Kishi, Shinya Uchida, Hisashi Nakahara, Hikaru Katano, Yoshikazu Ui
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Patent number: 11970977Abstract: 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: GrantFiled: August 26, 2022Date of Patent: April 30, 2024Assignee: Hamilton Sundstrand CorporationInventors: Murtuza Lokhandwalla, Brandon P. Williams, Jason A. Ryon, Todd Haugsjaahabink
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Patent number: 11970976Abstract: 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: GrantFiled: August 26, 2022Date of Patent: April 30, 2024Assignee: Hamilton Sundstrand CorporationInventors: Murtuza Lokhandwalla, Brandon P. Williams, Todd Haugsjaahabink, Charles E. Reuter, Jason A. Ryon, Kevin Gibbons, Jesse C. Peters
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Patent number: 11965424Abstract: 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: GrantFiled: June 21, 2022Date of Patent: April 23, 2024Assignee: General Electric CompanyInventors: Arthur William Sibbach, Brandon Wayne Miller, Erich Alois Krammer, Douglas Scott Jacobs, Joseph Alfred Iannotti
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Patent number: 11905898Abstract: 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: GrantFiled: December 19, 2019Date of Patent: February 20, 2024Assignee: The Boeing CompanyInventors: Jeffrey S. Siegmeth, David William Foutch, Bruce Van Deventer
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Patent number: 11891971Abstract: 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: GrantFiled: December 26, 2019Date of Patent: February 6, 2024Inventors: Fuminori Saito, Tokihiro Ikeda
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Patent number: 11879384Abstract: 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: GrantFiled: February 9, 2023Date of Patent: January 23, 2024Assignee: PRATT & WHITNEY CANADA CORP.Inventor: Sean Durand
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Patent number: 11867118Abstract: 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: GrantFiled: February 24, 2023Date of Patent: January 9, 2024Assignee: BJ Energy Solutions, LLCInventors: Tony Yeung, Ricardo Rodriguez-Ramon, Joseph Foster
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Patent number: 11859551Abstract: 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: GrantFiled: January 21, 2022Date of Patent: January 2, 2024Assignee: Hamilton Sundstrand CorporationInventors: Morgan O'Rorke, Todd Haugsjaahabink, Matej Rutar, Ryan Susca
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Patent number: 11828228Abstract: 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: GrantFiled: February 16, 2023Date of Patent: November 28, 2023Assignee: ROLLS-ROYCE plcInventors: Natalie C Wong, Thomas S Binnington, David A Jones, Daniel Blacker
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Patent number: 11761382Abstract: 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: GrantFiled: June 5, 2020Date of Patent: September 19, 2023Assignee: IHI CorporationInventor: Yasuhiko Yamamoto
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Patent number: 11746704Abstract: 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: GrantFiled: September 29, 2020Date of Patent: September 5, 2023Assignee: Mitsubishi Heavy Industries, Ltd.Inventors: Tomohiro Asai, Shohei Yoshida, Yoshitaka Hirata, Akinori Hayashi, Yasuhiro Akiyama, Yoshinori Matsubara
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Patent number: 11725585Abstract: 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: GrantFiled: November 30, 2021Date of Patent: August 15, 2023Assignee: Hamilton Sundstrand Corporation (HSC)Inventors: Ryan Susca, Todd Haugsjaahabink, Morgan O'Rorke
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Patent number: 11702990Abstract: 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: GrantFiled: September 8, 2021Date of Patent: July 18, 2023Assignee: Rolls-Royce North American Technologies Inc.Inventor: Alan W. Smith
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Patent number: 11674444Abstract: 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: GrantFiled: March 30, 2021Date of Patent: June 13, 2023Assignee: Hamilton Sundstrand CorporationInventors: Charles E. Reuter, Aaron F. Rickis, Francis P. Marocchini, Matej Rutar, August M. Coretto, Sachin Ramprashad
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Patent number: 11649768Abstract: 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: GrantFiled: August 20, 2021Date of Patent: May 16, 2023Assignee: Hamilton Sundstrand CorporationInventors: Todd Haugsjaahabink, Ryan Shook
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Patent number: 11629717Abstract: 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: GrantFiled: November 8, 2019Date of Patent: April 18, 2023Assignee: HAMILTON SUNDSTRAND CORPORATIONInventors: Charles E. Reuter, Gerald P. Dyer
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Patent number: 11629643Abstract: 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: GrantFiled: January 7, 2022Date of Patent: April 18, 2023Assignee: Hamilton Sundstrand CorporationInventor: Ryan Susca
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Patent number: 11499559Abstract: 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: GrantFiled: October 30, 2020Date of Patent: November 15, 2022Assignee: DELPHI TECHNOLOGIES IP LIMITEDInventors: Francisco Romo, Sonia Espinoza
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Patent number: 11466626Abstract: 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: GrantFiled: October 1, 2019Date of Patent: October 11, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventor: Cedrik Djelassi
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Patent number: 11391645Abstract: 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: GrantFiled: February 5, 2019Date of Patent: July 19, 2022Assignee: Weatherford Technology Holdings, LLCInventor: Domino Taverner
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Patent number: 11346239Abstract: 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: GrantFiled: September 18, 2020Date of Patent: May 31, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Shayan Ahmadian, Charles W. Haldeman, Mark F. Zelesky, Christopher T. Bergman, Sebastian Martinez
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Patent number: 11230979Abstract: 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: GrantFiled: March 8, 2019Date of Patent: January 25, 2022Assignee: PRATT & WHITNEY CANADA CORP.Inventors: David Waddleton, Benjamin Renaud, Sebastien Bergeron, Etienne Plamondon, Jean-Gabriel Gauvreau
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Patent number: 11191294Abstract: 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: GrantFiled: July 26, 2019Date of Patent: December 7, 2021Assignee: Ideal Snacks CorporationInventor: Steven Van Poucke
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Patent number: 11187154Abstract: 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: GrantFiled: March 13, 2019Date of Patent: November 30, 2021Assignee: Woodward, Inc.Inventors: Mark Allen Broome, Seth E. Rutan, Mark G. Goeddeke
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Patent number: 11187153Abstract: 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: GrantFiled: March 13, 2019Date of Patent: November 30, 2021Assignee: Woodward, Inc.Inventors: Mark Allen Broome, Seth E. Rutan, Mark G. Goeddeke
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Patent number: 11085375Abstract: 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: GrantFiled: June 15, 2017Date of Patent: August 10, 2021Assignee: General Electric CompanyInventors: Kihyung Kim, Anthony Whittenberg
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Patent number: 11067278Abstract: 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: GrantFiled: May 30, 2018Date of Patent: July 20, 2021Assignee: Delavan Inc.Inventors: Lev Alexander Prociw, Timothy Griffith
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Patent number: 10989118Abstract: 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: GrantFiled: December 20, 2018Date of Patent: April 27, 2021Assignee: WRIGHTSPEED, INC.Inventors: Ian Wright, Brandon Stitt
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Patent number: 10975805Abstract: 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: GrantFiled: July 11, 2017Date of Patent: April 13, 2021Assignee: AEROJET ROCKETDYNE, INC.Inventors: Douglas Parker, Frederick Dodd
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Patent number: 10801866Abstract: 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: GrantFiled: March 21, 2017Date of Patent: October 13, 2020Assignee: MTU FRIEDRICHSHAFEN GMBHInventors: Ludwig Kläser-Jenewein, Ulrich Meyer
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Patent number: 10598374Abstract: 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: GrantFiled: August 3, 2017Date of Patent: March 24, 2020Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Yen-Wen Wang, Nigel Davenport
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Patent number: 10428816Abstract: 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: GrantFiled: October 24, 2016Date of Patent: October 1, 2019Assignee: HAMILTON SUNDSTRAND CORPORATIONInventor: William E. Rhoden
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Patent number: 10393281Abstract: 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: GrantFiled: October 25, 2016Date of Patent: August 27, 2019Assignee: The Boeing CompanyInventors: Marcus Karel Richardson, David M. Smith
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Patent number: 10190774Abstract: 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: GrantFiled: December 23, 2014Date of Patent: January 29, 2019Assignee: General Electric CompanyInventors: Joshua Tyler Mook, Jason Joseph Bellardi, Ting-Yu Tu
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Patent number: 9920932Abstract: 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: GrantFiled: January 9, 2015Date of Patent: March 20, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Zhongtao Dai, Jeffrey M. Cohen, Catalin G. Fotache, Lance L. Smith, Donald J. Hautman
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Patent number: 9885355Abstract: 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: GrantFiled: September 25, 2015Date of Patent: February 6, 2018Assignee: SHOWA CORPORATIONInventors: Takahiko Saito, Atsushi Kagawa, Hayato Tsutsui