Having Fuel Supply System Patents (Class 60/734)
  • Patent number: 8302406
    Abstract: A fuel delivery and control system is provided including a dual pump fluid circuit configuration comprising a fixed positive displacement pump sized to supply the main engine burn flow ranging from above windmill through cruise, a positive displacement actuation pump including a variable pressure regulator, wherein the actuation pump is sized to supply fluid to engine actuators, valves and other hydraulically operated engine components and a pump flow sharing system interconnecting the two pumps. The combined flow from the two pumps is sufficient to meet the engine flow demand for windmill relight and maximum flow conditions. During cruise or normal operating conditions, the pumps operate in completely isolated flow circuits, minimizing recirculation and therefore heat input into the fuel supply system.
    Type: Grant
    Filed: October 15, 2008
    Date of Patent: November 6, 2012
    Assignee: Woodward, Inc.
    Inventor: Carthel C. Baker
  • Patent number: 8297036
    Abstract: A controller for a turbine power plant that is operable to identify a failure condition and measure a shutoff valve performance.
    Type: Grant
    Filed: June 11, 2008
    Date of Patent: October 30, 2012
    Assignee: United Technologies Corporation
    Inventors: Ruurd A. Vanderleest, Stuart S. Hay
  • Publication number: 20120266600
    Abstract: A fuel feed circuit for an aeroengine, the circuit including a high-pressure pumping system including first and second positive displacement pumps, a hydraulic actuator, and a fuel metering unit. As a function of a position of a slide of the actuator, a feed orifice of the actuator may be connected to a high-pressure delivery orifice connected to an outlet of the second pump, or to a low-pressure delivery orifice connected to a low-pressure feed line. The fuel metering unit includes through sections, one of these through sections being connected to an outlet of the high-pressure pumping system and the other through section being connected to an outlet of the high-pressure pumping system and leading to a high-pressure pilot chamber of the hydraulic actuator.
    Type: Application
    Filed: September 30, 2010
    Publication date: October 25, 2012
    Applicant: SNECMA
    Inventors: Nicolas Alain Bader, Frederic Brettes, Bastien Dore, Laurent Gilbert, Yves Hodinot
  • Publication number: 20120260658
    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: Application
    Filed: September 30, 2010
    Publication date: October 18, 2012
    Applicant: SNECMA
    Inventors: Nicolas Alain Bader, Regis Michel Paul Deldalle, Laurent Gilbert Yves Hodinot, Nicolas Potel
  • Patent number: 8286432
    Abstract: A turbine engine fuel supply system includes a priority flow line, a plurality of secondary fuel loads, a fluid-powered metering pump, a mechanically-driven fuel pump, and an electric machine. The fluid-powered metering pump, upon receiving fuel at its fuel inlet, rotates at a rotational speed, discharges the fuel from its fuel outlet at a flow rate dependent on the rotational speed, and supplies a first drive torque. The mechanically-driven fuel pump receives a second drive torque and, in response, draws fuel into its fuel inlet and discharges the fuel from its outlet to the fluid-powered metering pump fuel inlet to drive the fluid-powered metering fuel pump. The electric machine receives the first drive torque from the fluid-powered metering pump and generates electrical power.
    Type: Grant
    Filed: November 25, 2008
    Date of Patent: October 16, 2012
    Assignee: Honeywell International Inc.
    Inventor: Bruce Anson
  • Patent number: 8286414
    Abstract: A system and method to reduce the gas fuel supply pressure requirements of a gas turbine, which results in an increased operability range and a reduction in gas turbine trips. According to the method, the gas turbine is allowed to start and operate at supply pressures determined as a function of ambient conditions and gas turbine compressor pressure ratio. This increases the operability window, and reduces or eliminates the need for gas fuel compressors.
    Type: Grant
    Filed: June 1, 2009
    Date of Patent: October 16, 2012
    Assignee: General Electric Company
    Inventors: Brian Gallagher, Ravi Praveen S. Eluripati, Jonathan Carl Thatcher, Priscilla Childers, Bryan Edward Sweet
  • Publication number: 20120255310
    Abstract: A combustor nozzle includes a center body and a shroud circumferentially surrounding at least a portion of the center body to define a passage between the center body and the shroud. A guide between the center body and the shroud can pivot with respect to the center body. A method for supplying fuel to a combustor includes flowing a working fluid through a nozzle at a mass flow rate and flowing a fuel through the nozzle. The method further includes sensing a flame holding event inside the nozzle and pivoting a guide inside the nozzle to increase the mass flow rate of the working fluid flowing through the nozzle.
    Type: Application
    Filed: April 11, 2011
    Publication date: October 11, 2012
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Jason Thurman Stewart, Thomas Edward Johnson
  • Patent number: 8276387
    Abstract: A fuel conveying member of a gas turbine engine is described and includes a fuel manifold defining an annular fuel flow passage through a body of the fuel manifold. A plurality of fuel nozzles extend from the manifold in fluid flow communication with the annular fuel flow passage. The fuel manifold includes integral attachment lugs thereon for mounting the fuel manifold within the gas turbine engine. The attachment lugs are adapted to receive pins therein and provide a mounting mechanism which allows for thermal expansion of the fuel manifold relative to a surrounding support structure to which the fuel manifold is mounted via the attachment lugs.
    Type: Grant
    Filed: February 4, 2011
    Date of Patent: October 2, 2012
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Lev Alexander Prociw, Harris Shafique, Jason Fish, Bhawan B. Patel
  • Publication number: 20120234015
    Abstract: A fuel flow system for a gas turbine includes a first pump, a main fuel flow path and a second pump. The first pump is connected to an actuator and a metering valve. The main fuel flow path is formed between the first pump and the metering valve. The second pump is connected to the main fuel flow path and supplements the fuel flow from the first pump under certain conditions. The second pump and first pump are in parallel.
    Type: Application
    Filed: March 18, 2011
    Publication date: September 20, 2012
    Applicant: HAMILTON SUNDSTRAND CORPORATION
    Inventor: Charles E. Reuter
  • Patent number: 8256222
    Abstract: A fuel supply system includes a fuel metering pump and a servo-flow pump that are used to supply fuel to one or more fuel manifolds and one or more fluid-operated actuators, respectively. The fuel metering pump and the servo-flow pump are driven by the same electric motor(s).
    Type: Grant
    Filed: February 11, 2008
    Date of Patent: September 4, 2012
    Assignee: Honeywell International Inc.
    Inventors: Timothy D. Mahoney, Larry A. Portolese
  • Patent number: 8250849
    Abstract: Various embodiments of a fuel-control system for regulating the administration of a first fuel to a fuel consuming device are disclosed. In one aspect, the fuel-control system includes a system-controlling device adapted to consume a primary source of electrical power. The system controlling device is also adapted to consume a secondary source of electrical power, with the secondary source produced by noncombustibly consuming a second fuel.
    Type: Grant
    Filed: January 29, 2008
    Date of Patent: August 28, 2012
    Assignee: Sprint Communications Company L.P.
    Inventors: Julie Willets, Jason Brinkley, Jerry Meyers, Larry Johnson
  • Publication number: 20120210716
    Abstract: An aircraft fuel pumping arrangement comprises a first fuel pump, an electrically powered motor operable to drive the first fuel pump to deliver fuel to an outlet, a second fuel pump, a gas driven turbine operable to drive the second fuel pump to deliver fuel to the outlet, and a controller operable to control the operation of the gas driven turbine to determine the rate at which the second fuel pump is driven.
    Type: Application
    Filed: February 14, 2012
    Publication date: August 23, 2012
    Applicant: ROLLS-ROYCE GOODRICH ENGINE CONTROL SYSTEMS LTD.
    Inventors: Christopher John William Weir, Daniel James Bickley
  • Patent number: 8234870
    Abstract: A gas turbine engine fuel system includes a fuel tank for storing fuel, a heat exchanger through which the fuel from the fuel tank can pass, a fuel pump located downstream from the heat exchanger for pumping the fuel, a fuel metering unit for metering the fuel pumped by the fuel pump, an additive tank for storing a fuel additive, an additive delivery subsystem for mixing the fuel additive with the fuel at or before the heat exchanger to generate a fuel and fuel additive mixture, and a combustor located downstream of the fuel metering unit where the fuel and fuel additive mixture is delivered for combustion. The fuel additive comprises a fuel stabilizer for reducing fuel coking.
    Type: Grant
    Filed: April 17, 2009
    Date of Patent: August 7, 2012
    Assignee: Hamilton Sundstrand Corporation
    Inventor: Marc E. Gage
  • Patent number: 8234875
    Abstract: A fuel system for a turbine engine is provided. The fuel system includes a positive displacement pump driven by an electric motor. The pump is rotated in a first direction to deliver fuel to the turbine engine, and a second direction for evacuating fuel from the turbine engine. A shut-off check valve is open in a first direction in response to a first differential pressure created by the pump in the first direction. The shut-off check valve is biased to a closed position when the pump is rotating in the second direction. An ecology check valve is biased to a closed position in the first direction and open in the second direction in response to a second differential pressure created by the pump. The check valves open and close automatically in response to the pressures generated by the positive displacement pump in each of the first and second rotational directions. In this manner, simple, reliable valves are utilized to regulate the flow of fuel in the fuel system.
    Type: Grant
    Filed: August 5, 2011
    Date of Patent: August 7, 2012
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Charles H. Falke, Leo J. Veilleux, Douglas A. Parsons
  • Publication number: 20120186255
    Abstract: A system includes a fuel nozzle. The fuel nozzle includes a hub having an axis, a shroud disposed about the hub, an airflow path between the hub and the shroud, multiple vanes extending between the hub and the shroud, and a first fuel path leading to multiple first fuel outlets disposed on the multiple vanes. The fuel nozzle also includes a second fuel path leading to multiple second fuel outlets disposed on at least one of the hub and/or the shroud, wherein the multiple second fuel outlets are disposed at an axial distance upstream from a downstream end of the hub.
    Type: Application
    Filed: January 24, 2011
    Publication date: July 26, 2012
    Applicant: General Electric Company
    Inventors: Nishant Govindbhai Parsania, Ajay Pratap Singh
  • Publication number: 20120186263
    Abstract: A power-generation plant 10 including a gas turbine 11; a fuel-gas cooler 13; and an extraction line 24 that guides the fuel gas extracted from an intermediate stage of a fuel-gas compressor 12 to the fuel-gas cooler 13; a first level detector 61 that detects whether a level of the coolant accumulated at a bottom portion of the fuel-gas cooler 13 has reached a predetermined level; and a controller that stops the gas turbine 11 on the basis of a detection signal sent from the first level detector 61 and that outputs a command signal for stopping a coolant pump 53 that supplies the coolant to the spray nozzles 44 and 45.
    Type: Application
    Filed: January 20, 2012
    Publication date: July 26, 2012
    Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventor: Hiroshi Tanabe
  • Patent number: 8225610
    Abstract: A method of assembling a fuel delivery system is provided. The method includes providing a base that includes a surface, a receptacle extending into the base from the surface along a longitudinal axis, and a plurality of channels extending into the base from the receptacle. Each of the plurality of channels includes an inlet end and an outlet end, and each of the plurality of channels intersects the receptacle at the outlet end, wherein the receptacle and the plurality of channels are formed integrally within the base such that the plurality of outlet ends are spaced axially from one another. The method further includes securing a fuel nozzle within the receptacle, the fuel nozzle including a plurality of separate flow paths, wherein each of the plurality of channels is in flow communication with one of the plurality of separate flow paths.
    Type: Grant
    Filed: December 8, 2008
    Date of Patent: July 24, 2012
    Assignee: General Electric Company
    Inventors: James Eric Reed, Arthur S. Peck
  • Publication number: 20120180486
    Abstract: A combustor is provided and includes a center body having a tubular inner wall, a cartridge disposed within the tubular inner wall to define an outer annular space between an outer surface thereof and the tubular inner wall and an inner annular space having an open end and a closed end opposite the open end and an insert disposed within the outer annular space to envelop the cartridge proximate to the open end, the insert including a body having a tubular forward portion and a partially tubular aft portion, the partially tubular aft portion thereby forming a recessed track having a longitudinal axis substantially aligned with a longitudinal axis of the outer annular space.
    Type: Application
    Filed: January 18, 2011
    Publication date: July 19, 2012
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Kwanwoo Kim, Nishant Govindbhai Parsania, Dheeraj Sharma
  • Publication number: 20120174591
    Abstract: A fuel line system for a gas turbine and a method for purging the same is provided. Parts of the line system may be purged using a comparatively low quantity of purging medium.
    Type: Application
    Filed: September 23, 2010
    Publication date: July 12, 2012
    Inventors: Matthias Hase, Axel Mayr, Jürgen Meisl
  • Publication number: 20120174587
    Abstract: A fuel flowmeter for being fed by a pump including an inlet and an outlet, including: a metering valve including an inlet and an outlet, and arranged downstream from the outlet of the pump; a return circuit connecting the inlet of the metering valve to the inlet of the pump; and a pressure regulator device including: a movable valve member to close and open the return circuit, a pressure difference detection surface fastened to the valve member and axially separating a first chamber in communication with the inlet of the metering valve from a second chamber in communication with the outlet from the metering valve, a piston axially separating the second chamber from a third chamber connected to the outlet of the metering valve, and a channel putting the second chamber in communication with the third chamber.
    Type: Application
    Filed: August 26, 2010
    Publication date: July 12, 2012
    Applicant: TURBOMECA
    Inventors: Philippe Jean Rene Marie Benezech, Bruno Facca, Ludovic Alexandre Leglise, Cedric Roger Zordan
  • Publication number: 20120167569
    Abstract: Provided is a gas turbine combustion burner capable of uniformly ejecting fuel from ejection holes for reduced NOx emissions of gas turbine combustors. The gas turbine combustion burner includes a plurality of swirling vanes (20) for ejecting fuel from fuel ejection holes (23, 24) into air or a mixture of air and fuel flowing from an upstream side while applying a swirling force to form a swirling mixed airflow and a nozzle (21) having the swirling vanes (20) arranged radially on an outer circumferential surface thereof and having a first fuel passage (26), through which the fuel is guided to the fuel ejection holes (23, 24), provided therein, a cavity (25) communicating with the fuel ejection holes (23, 24) is provided in each swirling vane (20), and at least two second fuel passages (27) are provided between the cavity (25) and the first fuel passage (26) along an axial direction.
    Type: Application
    Filed: November 8, 2010
    Publication date: July 5, 2012
    Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Satoshi Takiguchi, Shinji Akamatsu, Kenji Sato, Naoki Abe
  • Publication number: 20120159953
    Abstract: A fuel staging system is described which comprises a staging valve 28 operable to divide a metered fuel supply between a pilot delivery line 18 and a mains delivery line 16, and a recirculation valve 54 connected to the mains delivery line 16 and operable to permit a recirculation fuel flow to be supplied to the mains delivery line 16 when the staging valve 28 occupies a position in which substantially no fuel is delivered to the mains delivery line 16 through the staging valve 28.
    Type: Application
    Filed: December 21, 2011
    Publication date: June 28, 2012
    Applicant: Rolls-Royce Goodrich Engine Control Systems Ltd.
    Inventors: Michael Griffiths, Jonathan David Pye
  • Patent number: 8205451
    Abstract: A system and assemblies for pre-heating fuel in a combined cycle power plant are provided. A fuel supply system includes a water heater assembly configured to heat a flow of water using progressively higher grade heat from a multi-stage heat exchanger arrangement. The fuel supply system also includes a fuel heater that includes a first flow path coupled in flow communication with a fuel flow path wherein the fuel heater includes a second flow path coupled in flow communication with a flow path for the flow of water. The fuel heater is configured to transfer heat from the flow of water to the flow of fuel.
    Type: Grant
    Filed: August 5, 2008
    Date of Patent: June 26, 2012
    Assignee: General Electric Company
    Inventors: Prakash Narayan, Shinoj Vakkayil Chandrabose
  • Patent number: 8196408
    Abstract: A turbomachine includes a compressor, a turbine operatively connected to the compressor, and a combustion assembly fluidly connected between the compressor and the turbine. The combustion assembly includes an end cover including a plurality of fuel circuits, a fuel distributing flange fluidly connected to at least one of the plurality of fuel circuits, a nozzle assembly fluidly linked to the at least one of the plurality of fuel circuits, and a fuel distribution system configured and disposed to deliver fuel to the fuel distributing flange. The fuel distribution system is selectively activated to stage fuel delivery to the at least one of the plurality of fuel circuits at a pressure sufficient to achieve atomization at the nozzle assembly without requiring a supplemental atomization air flow prior to delivering fuel to others of the plurality of fuel circuits at a pressure to achieve atomization without requiring a supplemental atomization air flow.
    Type: Grant
    Filed: October 9, 2009
    Date of Patent: June 12, 2012
    Assignee: General Electric Company
    Inventors: Sachin Khosla, Neal Spencer Birchfield, Mark William Pinson
  • Patent number: 8196409
    Abstract: A fuel supply arrangement for a gas turbine burner is provided. The fuel distribution arrangement includes a rear section external to the burner located between a turbine wall and a fuel distribution system interface directing fuel into fuel supply circuits. The fuel distribution system interface has four fuel connections. An intermediate section is located between the turbine wall and the backside wall of a distribution chamber; and a front section in front of the second section located between said backside wall of the distribution chamber and a burner central backside block. The fuel distribution arrangement includes pipes for gaseous fuel, liquid fuel, as well as pilot gas, and liquid pilot fuel. In the rear section the pipes for gaseous fuel and for liquid fuel are arranged concentrically, and in at least one portion of the intermediate section the pipe for gaseous fuel is arranged non-concentrically with the liquid fuel pipe.
    Type: Grant
    Filed: February 13, 2009
    Date of Patent: June 12, 2012
    Assignee: Alstom Technology Ltd
    Inventors: Damir Cankovic, Oliver Konradt, Albert Keller
  • Publication number: 20120137691
    Abstract: An assembly for a gas turbine is presented. The assembly includes a gas supply pipe passing through a bore in a flange of the gas turbine for supplying gas to a combustion chamber of the gas turbine and a sleeve surrounding the gas supply pipe, having a first end and a second end, wherein the first end is sealingly coupled to the gas supply pipe, and wherein the sleeve is adapted to be sealingly coupled to the flange at the second end such that the sleeve extends along a thickness of the flange.
    Type: Application
    Filed: December 1, 2010
    Publication date: June 7, 2012
    Inventors: Andreas Bõttcher, Timothy A. Fox, Daniel W. Garan, Thomas Grieb, Jens Kleinfeld, Tobias Krieger, Stephen A. Ramier, David M. Ritland, Marcus Zurhorst
  • Publication number: 20120137692
    Abstract: A gas turbine engine is provided. The gas turbine engine includes an air inlet, a combustor, an exhaust and first and second measurement devices. A plurality of fuel supply lines is provided to the at least one combustor. The first measurement device measures an amount of a gas in the air inlet. The second measurement device measures an amount of the gas in the exhaust. A control unit varies the fuel supply in the plurality of fuel supply lines so as to control the amount of the gas in the exhaust. The variation is made in dependence upon both the measured amount of the gas in the air inlet and the measured amount of the gas in the exhaust.
    Type: Application
    Filed: August 13, 2009
    Publication date: June 7, 2012
    Inventor: Robert Pearce
  • Patent number: 8186168
    Abstract: A method of at least partially balancing axial thrust loads and an engine in which the method is carried out is disclosed herein. The engine includes a combustion chamber and a fuel system operable to direct pressurized fuel to the combustion chamber. The engine also includes a rotor operable to rotate about a centerline axis and subjected to axial thrust loads during operation. The engine also includes a balance piston engaged with the rotor. The balance piston includes a pressure face positioned in a thrust cavity. The engine also includes a fluid passageway extending between the fuel system and the thrust cavity. Pressurized fuel is delivered to the pressure face to counteract axial thrust loads on the rotor.
    Type: Grant
    Filed: July 18, 2008
    Date of Patent: May 29, 2012
    Assignee: Rolls-Royce Corporation
    Inventor: Craig Heathco
  • Patent number: 8166762
    Abstract: Fuel control arrangements provide and control fuel flow to injectors through fuel control valves. The injectors are connected to respective fuel control valves which in turn are connected to a first fuel flow path. The injectors are also connected to a second fuel flow path. The fuel paths are associated with a fuel source and generally have a recirculation valve between them. When flow in the flow path is stopped, recirculation of fuel can be provided across the recirculation valve to prevent fuel degradation. By provision of a restrictor valve in the second fuel flow path control of fuel recirculation can be achieved, as well as greater flexibility by presenting fuel flow separately through the second flow path to the injector whilst the first flow path is inhibited.
    Type: Grant
    Filed: May 21, 2009
    Date of Patent: May 1, 2012
    Assignee: Rolls-Royce PLC
    Inventor: Mark Scully
  • Patent number: 8166765
    Abstract: A fuel delivery and control system is provided including a dual pump fluid circuit configuration comprising a fixed positive displacement pump sized to supply the main engine burn flow ranging from above windmill through cruise and a variable displacement pump sized to supply fluid to engine actuators, valves and other hydraulically operated engine components with a pump flow sharing system interconnecting the two pumps. The combined flow from the two pumps is sufficient to meet the engine flow demand for windmill relight and maximum flow conditions. During cruise or normal operating conditions, the pumps operate in completely isolated flow circuits, minimizing recirculation and therefore heat input into the fuel supply system.
    Type: Grant
    Filed: October 15, 2008
    Date of Patent: May 1, 2012
    Assignee: Woodward, Inc.
    Inventors: Carthel C. Baker, Joe F. Wollschlager
  • Publication number: 20120090331
    Abstract: Systems and methods for supplying fuel to a gas turbine are described. A fuel may be received, and one or more parameters associated with the received fuel may be determined. Based at least in part upon the determined one or more parameters, a desired pressure for removing one or more liquids from the fuel utilizing a separator may be calculated. The operation of a pressure changing device may then be controlled in order to achieve the desired pressure. In certain embodiments, the operations of the method may be performed by a controller that includes one or more computers.
    Type: Application
    Filed: October 18, 2010
    Publication date: April 19, 2012
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Timothy Russell Bilton, Daniel Martin Moss, Korey Frederic Rendo, Colin Wilkes
  • Patent number: 8156742
    Abstract: A fuel-injection device in a turbomachine is disclosed. The device includes a high-pressure pump supplying a flow control valve, whose outlet is connected via a pressurization and cut-off valve to a fuel-injector feed pipe. The valve is connected to the inlet and to the outlet of the pump in order to define two fuel pressurization thresholds, one of which is used to start-up and restart the turbomachine and the other is used for operating the turbomachine from an idle speed and for commanding an equipment with variable geometry.
    Type: Grant
    Filed: January 18, 2008
    Date of Patent: April 17, 2012
    Assignee: SNECMA
    Inventors: Frédéric Brettes, Jean Charles Cappellari, Laurent Gilbert Yves Hodinot, Sandrine Huet
  • Patent number: 8127548
    Abstract: A turbine engine fuel supply system includes a priority flow line, a plurality of secondary fuel loads, an electric fuel metering pump, and a mechanically-driven fuel pump. The priority flow line is used to supply fuel to one or more gas turbine engine fuel manifolds. The electric fuel metering pump has a fuel inlet and a fuel outlet, and is adapted to be selectively energized and, upon being energized, to draw fuel into its fuel inlet and discharge the fuel from its fuel outlet for supply to the priority flow line. The mechanically-driven fuel pump has a fuel inlet, and a fuel outlet that is in fluid communication with the electric fuel metering pump fuel inlet and the plurality of secondary fuel loads. As such, fuel may be supplied to the secondary fuel loads independent of the electric fuel metering pump, which advantageously reduces the electrical power consumption of the electric fuel metering pump.
    Type: Grant
    Filed: February 21, 2008
    Date of Patent: March 6, 2012
    Assignee: Honeywell International Inc.
    Inventors: Bruce Anson, Jay Sims, Jack Carpenter, William Nolan
  • Patent number: 8128378
    Abstract: A system and method is provided for controlling a variable displacement piston pump that supplies fluid to one or more loads. If fluid is being supplied through a metering valve to a load, then the variable displacement piston pump is controlled to operate in accordance with a variable flow/variable discharge pressure scheme. However, if fluid is not being supplied through the metering valve to the load, then the variable displacement piston pump is controlled to operate in accordance with a variable flow/constant discharge pressure scheme.
    Type: Grant
    Filed: November 21, 2007
    Date of Patent: March 6, 2012
    Assignee: Honeywell International Inc.
    Inventors: William Scott Rowan, Larry Portolese, Brad McRoberts, George Wieger
  • Patent number: 8122699
    Abstract: An ecology valve (EV) fuel return system includes a housing assembly, an ecology valve, and a fuel routing assembly. The ecology valve includes an EV piston slidably disposed within the housing assembly for movement between a fuel storage position and a fuel return position, a fuel storage chamber defined by the EV piston and the housing assembly, and an EV control chamber defined by the EV piston and the housing assembly. The fuel routing assembly, which is fluidly coupled to the EV control chamber and to the fuel storage chamber, is configured to route fuel: (i) from the fuel storage chamber to a fuel supply system when a gas turbine engine (GTE) is in a start-up mode, and (ii) from the first fuel manifold and from the EV control chamber to the fuel storage chamber when the GTE is in a shut-down mode.
    Type: Grant
    Filed: December 3, 2008
    Date of Patent: February 28, 2012
    Assignee: Honeywell International Inc.
    Inventors: David Lawrence, Paul Futa, Larry Portolese
  • Publication number: 20120042657
    Abstract: High-pressure fuel is supplied at a controlled rate to a combustion chamber via a position-controlled valve and a variable-restriction stop-and-pressurizing cut-off valve. A value representative of the real mass flow rate of fuel as delivered is calculated by a calculation unit on the basis of information representative of the pressure difference between the inlet and the outlet of the cut-off valve and of the flow section through the cut-off valve, e.g. as represented by the position X of the slide of the cut-off valve. The position-controlled valve has a variable position that is controlled by the calculation unit as a function of the difference between the calculated value representative of the real mass flow rate and a value representative of a desired mass flow rate.
    Type: Application
    Filed: April 15, 2010
    Publication date: February 23, 2012
    Applicant: SNECMA
    Inventors: Laurent Gilbert Yves Hodinot, Celine Marie Anne Issert, Pascal Laurent
  • Patent number: 8113001
    Abstract: A fuel injector for a secondary fuel nozzle in a gas turbine includes axially oriented air slots and a plurality of fuel injection holes disposed between the air slots. The plurality of fuel injection holes include axially oriented injection holes and radially oriented injection holes such that fuel input through the plurality of fuel injection holes is injected in both a radial direction and an axial direction to mix with air flowing through the air slots.
    Type: Grant
    Filed: September 30, 2008
    Date of Patent: February 14, 2012
    Assignee: General Electric Company
    Inventors: Arjun Singh, Swanand Vijay Sardeshmukh
  • Publication number: 20120023965
    Abstract: The present invention relates to a combustion controller for controlling the combustion of a flow of combustible and/or combusting fluid. The combustion controller comprises an inlet and an outlet which defines a flow path between them. A magnetic-field generator is arranged to generate a magnetic field across the flow path such that in use the fluid flows in the flow path through the magnetic field. As the fluid flows through the magnetic field an electric current is induced in the fluid. This results in energy being supplied to the fluid. This energy can assist is reignition. If the magnetic field is an alternating magnetic field then this induces an alternating current in the fluid. The frequency of this current can be controlled such that certain chemical reactions are either promoted or inhibited.
    Type: Application
    Filed: July 12, 2011
    Publication date: February 2, 2012
    Applicant: ROLLS-ROYCE PLC
    Inventors: Simon A. WEEKS, Christopher G. BRIGHT
  • Patent number: 8104258
    Abstract: The fuel system of a dual fuel turbine includes a flow control valve having a metering purge valve that in one state directly meters fuel to injectors of the turbine, in another state closes of fuel flow and passes purge air to the injectors and in another state positively closes of flow of both fuel and purge air. The metering purge valve is a pressure compensated spool valve that has a unique cross-ported interchange that passes fuel from the inlet through the spool to the metering edge. The direct metering of the valve to the injectors eliminates the need for additional shut off valves, and if used with a combining valve having an integral distributor section metering fuel to multiple injectors, the need for a separate flow divider is also eliminated. The valve can be actively cooled by dedicated coolant lines or lines shared with other flow control components such as additional metering valves for either the primary or secondary fuel.
    Type: Grant
    Filed: May 23, 2008
    Date of Patent: January 31, 2012
    Assignee: Jansen's Aircraft Systems Controls, Inc.
    Inventors: Harvey B. Jansen, Schuyler V. McElrath
  • Patent number: 8096129
    Abstract: A fuel distribution apparatus has a manifold head, a waisted portion and a nozzle head. An inlet channel is formed in a mounting surface of a casing of a jet engine. An annular inlet manifold is formed in the manifold head to receive fluid from the fuel inlet channel. Six outlet fluid passageways extend substantially tangentially away from the annular inlet manifold and open out into an annular outlet manifold. Three ports are formed in the inner wall of the annular outlet manifold and the ports are connected to fuel delivery tubes which extend away from the ports in a substantially helical fashion around the waisted portion into a nozzle head. The outlet fluid passageways are arranged to direct the fluid around the outlet manifold in a first direction and the helical fuel delivery tubes extend in the opposite direction.
    Type: Grant
    Filed: November 5, 2008
    Date of Patent: January 17, 2012
    Assignee: Rolls-Royce PLC
    Inventor: Oliver J. Francis
  • Patent number: 8096130
    Abstract: A gas turbine engine fuel conveying member in fluid flow communication with at least one fuel nozzle, the fuel conveying member having at least first and second member portions sealingly engaged to one another, and means for conveying fuel defined at a junction between the first and second member portions. The means for conveying fuel is defined by at least part of two different walls of each of the first and second member portions.
    Type: Grant
    Filed: July 20, 2006
    Date of Patent: January 17, 2012
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Oleg Morenko
  • Publication number: 20120006033
    Abstract: The present application provides for a combustor for use with a gas turbine engine. The combustor may include a cap member and a number of fuel nozzles extending through the cap member. One or more of the fuel nozzles may be provided in a non-flush position with respect to the cap member.
    Type: Application
    Filed: July 9, 2010
    Publication date: January 12, 2012
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Kwanwoo Kim, Thomas Edward Johnson, Jong Ho Uhm, Gilbert Otto Kraemer
  • Publication number: 20120006032
    Abstract: Certain embodiments of the invention may include systems, methods, and apparatus for confirming ignition in a gas turbine. According to an example embodiment of the invention, a method is provided for confirming ignition associated with a gas turbine combustor. The method can include receiving one or more permissive signals associated with one or more gas flow control valves, receiving one or more fuel supply pressure signals, receiving one or more fuel igniter signals, and receiving one ore more compressor pressure discharge (CPD) signals. The method can also include determining an ignition status associated with the gas turbine combustor based at least in part on the one or more permissive signals, the one or more fuel supply pressure signals, the one or more fuel igniter signals, and a qualified change in the one or more CPD signals. The method can also include outputting an ignition status signal based on the determined ignition status.
    Type: Application
    Filed: July 6, 2010
    Publication date: January 12, 2012
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Scott Alan Kopcho, Garth Curtis Frederick, Timothy Andrew Healy
  • Publication number: 20110314831
    Abstract: Emissions and combustion dynamics of a turbine engine are managed through a combustor system that injects water into the primary fuel flow and supplies a secondary water steam to the flame zone of the combustor through a central, secondary liquid nozzle or of the fuel nozzle assembly.
    Type: Application
    Filed: June 20, 2011
    Publication date: December 29, 2011
    Inventors: Khalil F. Abou-Jaoude, Stephen E. Mumford
  • Publication number: 20110296844
    Abstract: A gas turbine engine system, comprising a compressor, a combustor, and a turbine; a fuel system comprising one or more fuel circuits configured to provide fuel to the combustor; a non-catalytic fuel reformer in fluid communication with the one or more fuel circuits, wherein the non-catalytic fuel reformer is configured to receive an oxidant and a fraction of the fuel in the one or more fuel circuits in a fuel-rich ratio and reform the fraction of the fuel to produce a reformate; and a control system configured to regulate at least one of fuel flow and oxidizer flow to the non-catalytic fuel reformer to control a Modified Wobbe Index of the fuel entering the combustor.
    Type: Application
    Filed: June 2, 2010
    Publication date: December 8, 2011
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Stanley Kevin Widener, Mark Allan Hadley
  • Publication number: 20110289926
    Abstract: A turbomachine includes a compressor, a turbine, and a combustor operatively coupled to the compressor and the turbine. The combustor includes a combustor casing having a flange, an outer surface and an inner surface that defines an internal passage. The combustor casing includes an extruded fluid manifold mounted to the outer surface. The extruded fluid manifold includes first and second walls integrally formed with a third, connecting, wall. The first wall includes a first mounting element and the second wall includes a second mounting element. The first mounting element extends axially along the combustor casing away from the first wall and the second mounting element extends axially along the combustor casing away from the second wall and the first mounting element. The extruded fluid manifold is joined to the outer surface of the combustor casing through the first and second mounting elements.
    Type: Application
    Filed: June 1, 2010
    Publication date: December 1, 2011
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Brandon Taylor Overby, Jason Allen Seale, Ibrahim Ucok
  • Publication number: 20110289925
    Abstract: A fuel supply system for a gas turbine engine has a first pump for delivering fuel to a first use on a gas turbine engine, and a second pump for delivering fuel to a second use on the gas turbine engine. A valve allows flow from the first pump to be delivered to the first use, but also routes some flow from the first pump to supplement fuel flow from the second pump until a pressure downstream of the second pump increases. The valve then allows flow from the second pump to flow to the first use to supplement the flow from the first pump.
    Type: Application
    Filed: May 25, 2010
    Publication date: December 1, 2011
    Inventors: Gerald P. Dyer, Kevin Gibbons
  • Publication number: 20110289927
    Abstract: A fuel system of a burner of a gas turbine and to a method for flushing a section of a fuel system of a burner of a gas turbine is provided. The method includes providing a feed line for feeding liquid fuel from a fuel source to the burner, providing a first and a second connection point to the feed line, providing a medium at the first connection point and generating a vacuum at the second connection point such that the fuel which is situated in the section between the two connection points is sucked out through the second connection point.
    Type: Application
    Filed: January 22, 2010
    Publication date: December 1, 2011
    Inventor: Ulrich Wagner
  • Publication number: 20110283709
    Abstract: A method and a power plant for combustion of carbonaceous fuel for production of electrical power are described. The plant is a pressurized fluidized bed combustion plant wherein the compressor(s) (5, 5 . . . ) for compression of the air for the combustion is (are) arranged on shafts being separate from the shafts for the expander(s) (29) for expanding the combustion gas.
    Type: Application
    Filed: January 15, 2010
    Publication date: November 24, 2011
    Applicant: Sargas AS
    Inventor: Tor Christensen
  • Publication number: 20110277480
    Abstract: This system for supplying a turbine with liquid fuel comprises a liquid fuel inlet (3), a piping assembly (4) connecting the inlet to the turbine, and draining means for draining at least a portion of the said piping assembly. The draining means comprise water inlet means (9) and a system of controllable valves suitable for injecting water into at least one of the said portions of the piping assembly.
    Type: Application
    Filed: November 5, 2009
    Publication date: November 17, 2011
    Applicant: GE ENERGY PRODUCTS FRANCE SNC
    Inventors: Maher Aboujaib, Daniel Deloge