Having Fuel Supply System Patents (Class 60/734)
  • 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
  • Patent number: 9797313
    Abstract: An internal fuel manifold assembly includes a fuel manifold ring having at least one fuel conveying passage in fluid flow communication with at least one inlet passage defined through an inlet member. The inlet member is connected to the manifold ring proximate its first end and connected proximate its second end to at least one transfer tube. The inlet member includes a drainage passage for collecting possible leaked fuel from an annulus, defined between the inlet member and a heat shield surrounding the inlet member and spaced apart therefrom. Any leaked fuel is discharged out of the inlet member at an exit of the fuel passage on an end surface of the inlet member proximate the second end thereof.
    Type: Grant
    Filed: January 16, 2014
    Date of Patent: October 24, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Oleg Morenko
  • Patent number: 9777926
    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: October 3, 2017
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Zhongtao Dai, Jeffrey M. Cohen, Catalin G. Fotache, Lance L. Smith, Donald J. Hautman
  • Patent number: 9759096
    Abstract: Aspects of the invention provided herein include heat engine systems, methods for generating electricity, and methods for starting a turbo pump. In some configurations, the heat engine system contains a start pump and a turbo pump disposed in series along a working fluid circuit and configured to circulate a working fluid within the working fluid circuit. The start pump may have a pump portion coupled to a motor-driven portion and the turbo pump may have a pump portion coupled to a drive turbine. In one configuration, the pump portion of the start pump is fluidly coupled to the working fluid circuit downstream of and in series with the pump portion of the turbo pump. In another configuration, the pump portion of the start pump is fluidly coupled to the working fluid circuit upstream of and in series with the pump portion of the turbo pump.
    Type: Grant
    Filed: July 16, 2015
    Date of Patent: September 12, 2017
    Assignee: Echogen Power Systems, L.L.C.
    Inventor: Michael Louis Vermeersch
  • Patent number: 9650960
    Abstract: A fuel circuit for a turbine engine is provided. The fuel circuit includes a fuel return valve connected to the main circuit and to a fuel tank, the valve being capable of adopting an open position in which the valve allows an excess quantity of fuel to be returned to the tank, and a closed configuration in which the return of fuel to the tank is blocked; a first hydraulic line connecting the valve to the main circuit, and including a first filter; a second hydraulic line connecting the valve to the main circuit, and including a second filter; and an intermediate hydraulic line connected to the first and second lines downstream from the filters, the first and second lines being hydraulically connected together by the intermediate line when the valve is in the closed configuration.
    Type: Grant
    Filed: December 17, 2013
    Date of Patent: May 16, 2017
    Assignee: SNECMA
    Inventors: Philippe Vertenoeuil, Gilles Brun
  • Patent number: 9599042
    Abstract: A method for controlling fuel injection timing into a cylinder of an internal combustion engine having an internal control system based on ignition delay correlation wherein intake manifold pressure and oxygen concentration values are compared to steady state values of manifold pressure and oxygen concentration of a particular indicated torque set-point and engine speed. Comparing intake manifold pressure and oxygen concentration to steady state reference values further comprises experimentally determining exponential factors for intake manifold pressure factor and oxygen concentration factors. A multiplier for intake manifold pressure and oxygen concentration is determined taking into consideration the exponential factors for manifold pressure and oxygen concentration. An equation for correlation ignition delay is used to determine optional SOI timing.
    Type: Grant
    Filed: October 28, 2010
    Date of Patent: March 21, 2017
    Assignee: International Engine Intellectual Property Company, LLC.
    Inventors: Raj Kumar, William de Ojeda, James Rynold Popp
  • Patent number: 9587562
    Abstract: The present application provides a combustor for use with a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles and a fuel injection system for providing a flow of fuel to the micro-mixer fuel nozzles. The fuel injection system may include a number of support struts supporting the fuel nozzles and providing the flow of fuel therethrough. The support struts may include an aerodynamic contoured shape so as to distribute evenly a flow of air to the micro-mixer fuel nozzles.
    Type: Grant
    Filed: February 6, 2013
    Date of Patent: March 7, 2017
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Heath Michael Ostebee, Thomas Edward Johnson, Jason Thurman Stewart, Christopher Paul Keener
  • Patent number: 9500135
    Abstract: A fuel feed circuit for an aeroengine, the circuit including a high-pressure pumping system for delivering fuel at high pressure to combustion chamber injectors, the high-pressure pumping system including first and second positive displacement gear pumps driven simultaneously by the engine. A hydraulic switch member is interposed between respective outlets of the pumps, which makes it possible, in one state, to combine outlet flows from the two pumps to deliver fuel at high pressure to the combustion chamber injectors, and in another state, to discharge some or all of outlet flow from the first pump to a low-pressure feed line, an electrical control member serving to cause the hydraulic switch member to pass from one state to the other.
    Type: Grant
    Filed: September 30, 2010
    Date of Patent: November 22, 2016
    Assignee: SNECMA
    Inventors: Nicolas Alain Bader, Regis Michel Paul Deldalle, Laurent Gilbert Yves Hodinot, Nicolas Potel
  • Patent number: 9447975
    Abstract: The present application provides a combustor for use with a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles and a fuel injection system for providing a flow of fuel to the micro-mixer fuel nozzles. The fuel injection system may include a number of support struts supporting the fuel nozzles and for providing the flow of fuel therethrough. The fuel injection system also may include a number of aerodynamic fuel flanges connecting the micro-mixer fuel nozzles and the support struts.
    Type: Grant
    Filed: February 6, 2013
    Date of Patent: September 20, 2016
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Johnie Franklin McConnaughhay, Christopher Paul Keener, Thomas Edward Johnson, Heath Michael Ostebee
  • Patent number: 9429036
    Abstract: The present application provides a control valve actuator cooling system for providing a flow of cooling air to a control valve actuator. The control valve actuator cooling system may include a pressurized air source with the flow of cooling air, an air timing valve system, and a cooling air discharge port positioned about the control valve actuator such that the air timing valve system provides the flow of cooling air to the control valve actuator on an intermittent basis.
    Type: Grant
    Filed: September 24, 2013
    Date of Patent: August 30, 2016
    Assignee: General Electric Company
    Inventor: Jose Francisco Aguilar
  • Patent number: 9086017
    Abstract: A fuel injector includes a flow path for fuel air mixture to a combustor extending longitudinally through the fuel injector. The fuel injector may also include a liquid fuel gallery at least partially encircling the flow path. The gallery may include a plurality of fuel spokes configured to deliver liquid fuel from the gallery to the flow path. The fuel injector may also include an annular outer housing circumferentially positioned about the gallery to form an insulating air cavity at least partially around the gallery. The outer housing may include at least one purge hole to provide communication between the insulating air cavity and outside the outer housing of the injector.
    Type: Grant
    Filed: May 22, 2012
    Date of Patent: July 21, 2015
    Assignee: Solar Turbines Incorporated
    Inventors: Christopher Zdzislaw Twardochleb, Jonathan Gerrard Duckers
  • Publication number: 20150135724
    Abstract: A fuel pressure regulation system is provided. The fuel pressure regulation system includes a supply arrangement for supplying an outlet flow. The supply arrangement includes a primary pressure regulator and a bypass pressure regulator. The primary pressure regulator is operably connected to downstream pressures of each of a plurality of parallel metering circuits. The bypass pressure regulator is upstream from an output of a pump or pumps, which in combination with the primary pressure regulator, is operable to increase the output of the pump or pumps to accommodate for downstream pressure spikes in any one of the parallel metering circuits.
    Type: Application
    Filed: November 18, 2014
    Publication date: May 21, 2015
    Applicant: Woodward, Inc.
    Inventor: Carthel C. Baker
  • Publication number: 20150135723
    Abstract: A combustor nozzle includes a fuel passage that extends generally axially in the nozzle and a surface that extends radially across at least a portion of the fuel passage. A projection in the surface extends generally axially down-stream from the surface, and an indention in the surface radially surrounds the projection. An oxidant supply is in fluid communication with an oxidant passage, and the oxidant passage is radially displaced from the fuel passage and terminates at an oxidant outlet. A method of supplying a fuel to a combustor includes flowing fuel through a projection in a surface, wherein the projection extends generally axially downstream from the surface, and flowing fuel through an indention in the surface, wherein the indention radially surrounds the projection. The method further includes flowing an oxidant through an oxidant outlet that circumferentially surrounds the indention in the surface.
    Type: Application
    Filed: February 21, 2012
    Publication date: May 21, 2015
    Applicant: General Electric Company
    Inventors: Vladimir Vasilyevich Belyaev, Gilber Otto Kraemer, Predrag Popovic
  • Publication number: 20150128599
    Abstract: One embodiment of the present disclosure is a gas turbine engine. Another embodiment is a unique combustion system. Another embodiment is a unique engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for employing continuous detonation combustion processes. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.
    Type: Application
    Filed: March 14, 2014
    Publication date: May 14, 2015
    Inventor: Philip H. Snyder
  • Publication number: 20150128606
    Abstract: The present application provides a pilot manifold system for a combustor of a gas turbine engine. The pilot manifold system may include a casing with a casing manifold, an end cover connected to the casing and having an end cover passage in communication with the casing manifold, and a fuel nozzle mounted about the end cover. The fuel nozzle may include a pilot system in communication with the end cover passage.
    Type: Application
    Filed: November 11, 2013
    Publication date: May 14, 2015
    Applicant: General Electric Company
    Inventors: Bryan Wesley Romig, Brandon Taylor Overby
  • Publication number: 20150121887
    Abstract: A method of controlling operability of a gas turbine during part-speed operation includes identifying that a combustion system of the gas turbine is operating at part-speed, the combustion system including a fuel source, fuel circuits and valves operably interposed between the fuel source and the fuel circuits, respectively, defining first and second boundaries based on first and second parameters and automatically controlling each of the valves to control fuel flow to each of the fuel circuits in accordance with the defined first and second boundaries.
    Type: Application
    Filed: November 4, 2013
    Publication date: May 7, 2015
    Applicant: General Electric Company
    Inventors: Chi Ming Ho, Skigh Elliot Lewis, Priscilla Graves Childers, David Leach
  • Publication number: 20150101339
    Abstract: A fuel system for a gas turbine engine, which includes a combustor section and an actuator, includes a fuel source, a combustor system, and an actuation system. The combustor system includes a combustor pump that is fluidly connected to the fuel source and to the combustor section, with the combustor pump being mechanically connected to and powered by an electric motor. The actuation system includes an actuator pump that is fluidly connected to the fuel source and to the actuator, with the actuator pump being mechanically connected to and powered by a gearbox or an electric motor.
    Type: Application
    Filed: February 19, 2014
    Publication date: April 16, 2015
    Applicant: Hamilton Sundstrand Corporation
    Inventor: Leo J. Veilleux, JR.
  • Patent number: 8991190
    Abstract: A method for transferring fuel includes flowing water to at least one nozzle of a main fuel circuit. Also included is flowing oil to the at least one nozzle of the main fuel circuit. Further included is flowing liquid fuel to the at least one nozzle of the main fuel circuit, wherein flowing water to the at least one nozzle of the main fuel circuit occurs prior to flowing oil to the at least one nozzle of the main fuel circuit and flowing liquid fuel to the at least one nozzle of the main fuel circuit.
    Type: Grant
    Filed: January 31, 2012
    Date of Patent: March 31, 2015
    Assignee: General Electric Company
    Inventors: Hua Zhang, Douglas Frank Beadie, Gregory Allen Boardman, Geoffrey David Myers
  • Patent number: 8991148
    Abstract: A jet pump (14) is inserted between the low-pressure pump and a high-pressure fuel pump (16). A fuel metering unit (20) includes a metering valve (22) which delivers a regulated fuel flow to a feed line (30), and a bypass valve (24) which diverts to a primary intake (14a) of the jet pump the excess fuel flow supplied by the high-pressure pump. An overspeed protection unit (50) includes a control element (54) of the bypass valve (24) which causes said to fully open in the event of an overspeed of the engine. A shutoff and pressurization checkvalve (42) is mounted on the feed line and controlled by a servo-valve (44) having a high-pressure port (44a) brought to the high fuel pressure, a low-pressure port brought to the pressure of the primary intake (14a) of the jet pump and an output setting the pressure in a control chamber (42a) of the shutoff valve (42) to a value between those prevailing at the high pressure and low pressure ports.
    Type: Grant
    Filed: April 15, 2011
    Date of Patent: March 31, 2015
    Assignee: SNECMA
    Inventors: Bastien Dore, Loïc Pora
  • Patent number: 8991186
    Abstract: A fuel control system comprises a metering valve operable to control the flow of fuel between a supply line and a delivery line, a spill valve operable to control fuel flow within the supply line, a pressure raising valve connected to the delivery line, and a control servo valve movable between a thrust control mode in which it modifies the control of the spill valve to reduce the fuel flow delivered via the metering valve and an outlet of the pressure raising valve, and a windmill relight position in which it modifies the control of the pressure raising valve to allow fuel delivery through the outlet of the pressure raising valve at a reduced system pressure.
    Type: Grant
    Filed: December 8, 2010
    Date of Patent: March 31, 2015
    Assignee: Rolls-Royce Engine Control Systems Limited
    Inventors: Daniel James Bickley, Michael Griffiths
  • Publication number: 20150082795
    Abstract: An aft frame for a transition duct of a gas turbine combustor includes a main body having an outer rail, an inner rail, a first side rail circumferentially separated from an opposing second side rail, a forward portion, an aft portion and an outer surface. An inlet port extends through the outer surface and an exhaust port extends through the forward portion. A serpentine cooling passage is defined within the main body beneath the outer surface. The serpentine cooling passage is in fluid communication with the inlet port and the exhaust port. A conduit may be connected to the exhaust port for routing a compressed working fluid away from aft frame.
    Type: Application
    Filed: September 25, 2013
    Publication date: March 26, 2015
    Applicant: General Electric Company
    Inventors: Elizabeth Angelyn Fadde, Patrick Benedict Melton, David William Cihlar, Richard Martin DiCintio
  • Patent number: 8984856
    Abstract: An example fuel system includes a fuel sensor configured to sense at least one characteristic of a fuel provided to an engine. The fuel is selected from a plurality of different fuel types. The fuel system also includes a controller that is configured to meter the fuel in response to the at least one characteristic of the fuel.
    Type: Grant
    Filed: February 3, 2011
    Date of Patent: March 24, 2015
    Assignee: Hamilton Sundstrand Corporation
    Inventor: William E. Rhoden
  • Publication number: 20150075170
    Abstract: Systems and methods for operating a gas turbine combustion system by generating a flame detection signal are provided. A set of modeled parameters expected when there is a flame in a secondary combustion zone is calculated. A set of measured gas turbine parameters is measured. A flame validation signal based on the set of measured parameters and the set of modeled parameters is generated. The systems include a subsystem that calculates a set of modeled parameters expected when there is a flame in the secondary combustion zone and a subsystem that measures a set of measured parameters. A subsystem generates a flame validation signal based on the set of measured parameters and the set of modeled parameters.
    Type: Application
    Filed: September 17, 2013
    Publication date: March 19, 2015
    Applicant: General Electric Company
    Inventors: Alston Ilford Scipio, Sanji Ekanayake, Dale J. Davis, Jean-Marc Carré, William McEntagart
  • Patent number: 8978383
    Abstract: A fuel manifold assembly for a gas turbine engine is described and includes an annular manifold body and an annular heat shield assembly mounted to and surrounding the manifold body. The heat shield assembly has an inner surface facing the manifold body and spaced apart therefrom by an inner air gap, which substantially surrounds the manifold body, defined therebetween. The heat shield assembly has an outer surface facing away from the manifold body and spaced apart from the inner surface by an outer air gap substantially surrounding the inner air gap. At least the outer air gap is formed by a double wall configuration of the heat shield assembly.
    Type: Grant
    Filed: March 26, 2012
    Date of Patent: March 17, 2015
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Bhawan B. Patel, Oleg Morenko
  • Patent number: 8973368
    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 26, 2011
    Date of Patent: March 10, 2015
    Assignee: United Technologies Corporation
    Inventors: Zhongtao Dai, Jeffrey M. Cohen, Catalin G. Fotache, Lance L. Smith, Donald J. Hautman
  • Patent number: 8973366
    Abstract: A system includes a mixing assembly configured to mix a liquid fuel and a water to generate a fuel mixture. The fuel mixture is configured to combust in a combustor of a gas turbine. The mixing assembly includes a liquid fuel passage disposed in an integrated housing. The liquid fuel passage is configured to flow the liquid fuel and to exclude liquid traps. The mixing assembly also includes a water passage disposed in the integrated housing. The water passage is configured to flow the water and to exclude liquid traps. The mixing assembly also includes a mixer disposed in the integrated housing and coupled to the liquid fuel passage and the water passage. The mixer is configured to mix the liquid fuel and the water to form the fuel mixture.
    Type: Grant
    Filed: October 24, 2011
    Date of Patent: March 10, 2015
    Assignee: General Electric Company
    Inventors: Hua Zhang, Douglas Frank Beadie, Douglas Scott Byrd, Fabien Thibault Codron, James Frederik den Outer, Mark Jason Fisher
  • Patent number: 8966904
    Abstract: An architecture for feeding fuel to a power plant (1) of a rotorcraft, which power plant comprises a plurality of engines (2, 3) individually fed with fuel by respective assemblies (4, 5). Each assembly (4, 5) comprises a fuel feed circuit (9, 10) for feeding a safe tank (6, 7) from a fuel tank (8) that is common to the assemblies (4, 5). Together the feed circuits (9, 10) form a circuit for forced both-way transfer of fuel from either one of the assemblies to the other via the common tank (8) and an intercommunication (21) interposed between the safe tanks (6, 7), which safe tanks are fitted with respective spillage devices (17, 18, 19, 20) for transferring excess fuel to the common tank (8).
    Type: Grant
    Filed: August 21, 2012
    Date of Patent: March 3, 2015
    Assignee: Airbus Helicopters
    Inventors: Lionel Lollini, Damien Morizot
  • Publication number: 20150052909
    Abstract: A fuel control module including a gas vent manifold is disclosed. The gas vent manifold includes a first gas vent portion including a first gas vent connection and a second gas vent portion including a second gas vent connection. The gas vent manifold also includes a condensation portion extending between the first gas vent portion and the second gas vent portion. The gas vent manifold further includes a condensation drain port fluidly connected to the condensation portion. The gas vent manifold also includes a plurality of connection ports. Each connection port is configured to fluidly couple the gas vent manifold to a vent line of one or more pneumatic valves.
    Type: Application
    Filed: August 21, 2013
    Publication date: February 26, 2015
    Applicant: SOLAR TURBINES INCORPORATED
    Inventors: Darren Matthew Stratton, Behnood Miri
  • Publication number: 20150052905
    Abstract: Systems and methods for pulse-width modulation of late lean liquid injection velocity can be provided by certain embodiments of the disclosure. In one embodiment, a gas turbine combustor utilizing a late lean injection scheme can be provided, wherein the combustor can include a combustor liner and a transition piece. Methods described herein can allow for dynamic and intelligent adjustment of the late lean injection scheme based on a duty cycle and, optionally, a measured combustion gases temperature profile. The adjustments can involve a pulse-width modification of the duty cycle, which in turn can affect a fuel introduction velocity. Dynamic control of the fuel introduction velocity can provide for improved fuel droplet penetration and moving the heat release zone away from walls of the transitional piece.
    Type: Application
    Filed: August 20, 2013
    Publication date: February 26, 2015
    Applicant: General Electric Company
    Inventors: William Francis Carnell, JR., Ilya Aleksandrovich Slobodyanskiy
  • Patent number: 8959923
    Abstract: An arrangement for preparation of a fuel for combustion including a burner is provided. The arrangement includes a combustion chamber associated with the burner and in which combustion of a fuel is to take place, as well as means for supplying liquid fuel to the arrangement through an internal passage in the burner for the combustion, solid portions of the burner body being heated by the combustion, wherein the internal passage is located inside the solid portions of the burner body for receiving heat energy evaporating the fuel from these body portions, and that it includes means for conveying vaporized fuel to the combustion chamber to take part in the combustion.
    Type: Grant
    Filed: February 20, 2012
    Date of Patent: February 24, 2015
    Assignee: Siemens Aktiengesellschaft
    Inventors: Ulf Nilsson, Peter Senior
  • Patent number: 8959920
    Abstract: An assembly or system is provided for selectively regulating journal bearing lubrication between at least first and second levels in an aircraft engine. A high pressure pump includes movable portions at least in part supported by a journal bearing. A selector valve is configured to selectively supply lubrication flow to the journal bearing. In addition, a relief valve is configured to receive a signal from the selector valve defining a pressure level at which the relief valve should relieve pressure.
    Type: Grant
    Filed: April 13, 2012
    Date of Patent: February 24, 2015
    Assignee: Eaton Corporation
    Inventor: Martin A. Clements
  • Publication number: 20150047364
    Abstract: The invention relates to a burner arrangement for using in a single combustion chamber or in a can-combustor comprising a center body burner located upstream of a combustion zone, an annular duct with a cross section area, intermediate lobes which are arranged in circumferential direction and in longitudinal direction of the center body. The lobes being actively connected to the cross section area of the annular duct, wherein a cooling air is guided through a number of pipes within the lobes to the center body and cools beforehand at least the front section of the center body based on impingement cooling. Subsequently, the impingement cooling air cools the middle and back face of the center body based on convective and/or effusion cooling. At least the back face of the center body includes on the inside at least one damper.
    Type: Application
    Filed: July 29, 2014
    Publication date: February 19, 2015
    Inventors: Xianfeng Gao, Urs Benz, Andre Theuer, Rohit Kulkarni
  • Publication number: 20150040571
    Abstract: A method for controlling fuel splits to a controller is provided that includes comparing a combustor operating parameter to a predefined combustor operating parameter range. If the combustor operating parameter is outside its respective range, then a modified turbine firing temperature is calculated. The modified turbine firing temperature may then be used to determine the fuel splits to the combustor using a nominal fuel splits lookup table.
    Type: Application
    Filed: August 7, 2013
    Publication date: February 12, 2015
    Applicant: General Electric Company
    Inventor: Nilanjan Prosad Coomar
  • Patent number: 8950186
    Abstract: A system and method for supplementing fuel feed pressure and flow within an aircraft fuel system. The fuel system includes boost and override fuel pumps delivering fuel from the tanks to a fuel manifold, and a jettison fuel pump. The method includes the steps of: (a) sensing whether the aircraft engine is operating near maximum power; (b) upon sensing the condition, operating the jettison fuel pump in fluid interconnection with the override fuel pump to deliver fuel to the fuel manifold; and (c) upon sensing the cessation of the condition, deactivating the jettison fuel pump. The system includes a monitoring circuit signaling when the aircraft engine speed is greater than a predetermined threshold, and a fuel system control circuit operating a jettison fuel pump enable circuit portion in response to the signal while omitting other jettisoning operations. The jettison fuel pump consequently functions as an override fuel pump assist.
    Type: Grant
    Filed: September 11, 2011
    Date of Patent: February 10, 2015
    Assignee: The Boeing Company
    Inventor: William H. McCabe