Having Fuel Supply System Patents (Class 60/734)
  • Publication number: 20140331674
    Abstract: A wake reducing structure for a turbine system includes a combustor liner having an inner surface and an outer surface, the inner surface defining a combustor chamber. Also included is an airflow path located along the outer surface of the combustor liner. Further included is a wake generating component disposed in the airflow path and proximate the combustor liner, wherein the wake generating component generates a wake region located downstream of the wake generating component. Yet further included is an airfoil at least partially disposed in the wake region, the airfoil comprising at least one airfoil hole.
    Type: Application
    Filed: May 8, 2013
    Publication date: November 13, 2014
    Applicant: General Electric Company
    Inventors: Chandrasekhar Pushkaran, Nishant Govindbhai Parsania, Arjun Singh
  • Publication number: 20140331685
    Abstract: A gas engine assembly includes a compressor, a combustion system, a bypass line and a control system. The control system is configured to control gas supply parameters based on a transportation delay value. The transportation delay value corresponds to a delay between a time when a gas supply control mechanism is adjusted and a time that gas having a corresponding adjustment of a gas characteristic is received at a predetermined point downstream from the gas supply control mechanism.
    Type: Application
    Filed: May 10, 2013
    Publication date: November 13, 2014
    Applicant: General Electric Company
    Inventors: Oscar Eduardo Sarmiento Penuela, Raphael Rupert Burgmair, Johannes Huber, Medy Satria, Rosa Castane Selga, Prashant Srinivasan
  • Patent number: 8881529
    Abstract: A gas turbine, in particular a gas turbine aircraft engine, including a fuel supply device and a control device, wherein at least parts of the control device, in particular of an engine control device, are integrated into the fuel supply device.
    Type: Grant
    Filed: May 9, 2007
    Date of Patent: November 11, 2014
    Assignee: MTU Aero Engines GmbH
    Inventor: Peter Wittmann
  • Publication number: 20140318134
    Abstract: A system for supplying a gaseous fuel to a gas turbine includes a liquefied fuel source for supplying a liquefied fuel to a liquid fuel pump that is disposed downstream from the liquefied fuel source. The liquid fuel pump is sufficient to raise the pressure of the liquefied fuel to a substantially supercritical pressure. A supercritical liquefied fuel vaporizer is disposed downstream from the liquid fuel pump. A heat recovery system is in thermal communication with the liquefied fuel. The heat recovery system is positioned between the liquid fuel source and the supercritical liquefied fuel vaporizer.
    Type: Application
    Filed: April 24, 2013
    Publication date: October 30, 2014
    Applicant: General Electric Company
    Inventor: Predrag Popovic
  • Publication number: 20140305126
    Abstract: An apparatus for equalizing flow velocity distribution of a fuel gas supplied into a catalytic combustor includes a rectification vane and a rectification plate in an inlet chamber of the catalyst combustor. The inlet chamber has a round transverse sectional shape and includes an inflow port that allows the fuel gas to inflow radially, and an outflow port for discarding the fuel gas axially. The rectification vane has a front edge oriented towards the inflow port, and a rectifying surface ramified from the front edge so as to extend towards a cylindrical inner wall surface of the inlet chamber such that swirling flow of the fuel gas flown into the inlet chamber, that flows towards the inflow port along the cylindrical inner wall surface, is generated. The rectification plate is located at the outflow port and has openings for allowing the fuel gas to flow therethrough.
    Type: Application
    Filed: June 27, 2014
    Publication date: October 16, 2014
    Applicant: KAWASAKI JUKOGYO KABUSHIKI KAISHA
    Inventors: Yasushi DOURA, Masahiro OGATA, Kousuke TANAKI
  • Patent number: 8857150
    Abstract: A device and method for monitoring a high-pressure pump in a turbomachine fuel supply circuit by detecting opening of a pressurizing and shut-off valve mounted on an outlet side of a fuel flow regulating valve, by measuring rotational speed of the turbomachine corresponding to the opening of the pressurizing and cut-off valve, and by monitoring change in a value of the rotational speed to propose replacement of the high-pressure pump when the measure value rotational speed reaches a predetermined threshold.
    Type: Grant
    Filed: November 18, 2008
    Date of Patent: October 14, 2014
    Assignee: SNECMA
    Inventors: Christian Aurousseau, Jonathan Benitah, Xavier Flandrois, Jean-Remi Masse, Mickael Sauzedde, Franck Godel, Julien Maille
  • Publication number: 20140298814
    Abstract: A system for pre-heating a working fluid within a combustor includes a compressor for providing the working fluid to the combustor. An outer casing is disposed downstream from the compressor. The outer casing at least partially defines a high pressure plenum that at least partially surrounds the combustor. A combustion chamber is defined within the combustor downstream from the high pressure plenum. A catalytic combustor is disposed within the high pressure plenum upstream from the combustion chamber so as to provide thermal energy to the working fluid upstream from the combustion chamber.
    Type: Application
    Filed: April 8, 2013
    Publication date: October 9, 2014
    Applicant: General Electric Company
    Inventors: John Anthony Conchieri, Roy Marshall Washam, Gilbert Otto Kraemer
  • Publication number: 20140298819
    Abstract: A turbine engine for an aircraft including a turbine engine shaft and a pumping module, including: a pump shaft, connected to the turbine engine shaft; a pump for supplying fuel to the turbine engine, mounted on the pump shaft, configured to deliver a flow of fuel as a function of a speed of rotation of the turbine engine shaft; and an electrical device mounted on the pump shaft and configured, according to a first mode of operation, to drive the pump shaft in rotation to actuate the supply pump and, according to a second mode of operation, to be driven in rotation by the pump shaft to supply electrical power to equipment of the turbine engine.
    Type: Application
    Filed: November 28, 2012
    Publication date: October 9, 2014
    Applicant: TURBOMECA
    Inventors: Jean Lindeman, Philippe Jean, René, Marie Benezech, Jean-Luc Charles, Gilbert Frealle, Bertrand Moine
  • Publication number: 20140298818
    Abstract: A method and a device for controlling a lean fuel intake gas turbine engine, which can stably maintain operation of the gas turbine engine by preventing misfire and burnout of a catalytic combustor even when a catalyst in the combustor is deteriorated. A difference between measured temperatures of an inlet and an outlet of the combustor with respect to a methane concentration in an intake gas that is to be taken into the lean fuel intake gas turbine engine is compared with reference temperature difference data that is data indicating difference between temperatures of the inlet and the outlet of the combustor including a catalyst in its initial state to be a reference, and at least one of the inlet temperature and the outlet temperature of the combustor is controlled based on a difference between the measured temperature difference and the reference temperature difference data.
    Type: Application
    Filed: June 19, 2014
    Publication date: October 9, 2014
    Applicant: KAWASAKI JUKOGYO KABUSHIKI KAISHA
    Inventors: Soh KUROSAKA, Yoshihiro YAMASAKI, Yasushi DOURA
  • Patent number: 8850818
    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: Grant
    Filed: October 18, 2010
    Date of Patent: October 7, 2014
    Assignee: General Electric Company
    Inventors: Timothy Russell Bilton, Daniel Martin Moss, Korey Frederic Rendo, Colin Wilkes
  • Publication number: 20140290266
    Abstract: A fuel system for an aircraft comprises a boost pump, a main fuel pump and a motive pump. The boost pump receives fuel from a storage unit. The main fuel pump receives fuel from the boost pump and delivers fuel to a distribution system. The motive fuel pump receives fuel from the boost pump, routes fuel through the storage unit, and delivers fuel to an actuator.
    Type: Application
    Filed: March 27, 2013
    Publication date: October 2, 2014
    Applicant: Hamilton Sundstrand Corporation
    Inventors: Leo J. Veilleux, JR., Gary M. McBrien
  • Patent number: 8844293
    Abstract: A method and apparatus for heating fuel in an aircraft gas turbine engine, for example to provide fuel anti-icing to the fuel, comprises directing a fuel flow through a heat exchanger associated with a generator power conditioning unit as a sole means for providing anti-icing heating to fuel supplied for engine combustion. The method and apparatus permits the heat exchanger to heat the fuel sufficiently so that other dedicated heating means may be unnecessary.
    Type: Grant
    Filed: March 22, 2011
    Date of Patent: September 30, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Ian A. MacFarlane
  • Patent number: 8844292
    Abstract: A method for purging fuel from a fuel system of a gas turbine engine on shutdown of the engine comprises, in one aspect, terminating a fuel supply to the fuel system and using the residual compressed air to create a reversed pressure differential in the fuel system relative to a forward pressure differential of the fuel system used to maintain fuel supply for engine operation, and under the reversed pressure differential substantially purging the fuel remaining in the system therefrom to a fuel source.
    Type: Grant
    Filed: May 15, 2014
    Date of Patent: September 30, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Kevin Allan Dooley
  • Publication number: 20140283525
    Abstract: A gas turbine engine combustion system including a mixing duct that separates into at least two branch passages for the delivery of a fuel and working fluid to distinct locations within a combustion chamber. The residence time for the fuel and working fluid within each of the two branch passages is distinct.
    Type: Application
    Filed: May 9, 2014
    Publication date: September 25, 2014
    Applicant: Rolls-Royce Canada, Ltd.
    Inventor: Thomas Scarinci
  • Publication number: 20140260270
    Abstract: A gas turbine engine that includes: an interior flowpath defined through a combustor and a turbine; an aft frame forming an interface between the combustor the turbine, the aft frame comprising a rigid structural member that circumscribes the interior flowpath, wherein the aft frame includes an inner wall that defines an outboard boundary of the interior flowpath; a circumferentially extending fuel plenum formed through the aft frame; and outlet ports formed through the inner wall of the aft frame. The outlet ports may be configured to connect the fuel plenum to the interior flowpath.
    Type: Application
    Filed: March 15, 2013
    Publication date: September 18, 2014
    Applicant: General Electric Company
    Inventor: General Electric Company
  • Publication number: 20140260301
    Abstract: A fuel system for a gas turbine engine includes an engine fuel manifold, a hydraulic actuator, and a drain piston assembly. The hydraulic actuator actuates in response to a change in pressures within the hydraulic actuator. The drain piston assembly is fluidically connected to both the hydraulic actuator and the engine fuel manifold. The drain piston assembly receives fuel from the engine fuel manifold and sends fuel to the hydraulic actuator during engine shut down.
    Type: Application
    Filed: March 14, 2013
    Publication date: September 18, 2014
    Applicant: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Todd Haugsjaahabink, Charles E. Reuter
  • Publication number: 20140260260
    Abstract: A gas turbine engine comprises a combustor. The combustor comprises an annular combustor chamber formed between an inner liner and an outer liner spaced apart from the inner liner. An annular fuel manifold has fuel nozzles distributed circumferentially on the fuel manifold, the fuel manifold and fuel nozzles positioned entirely inside the combustion chamber.
    Type: Application
    Filed: March 12, 2013
    Publication date: September 18, 2014
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventor: Oleg Morenko
  • Publication number: 20140260262
    Abstract: A gas turbine that includes: a combustor coupled to a turbine that together define an interior flowpath, the interior flowpath extending aftward about a longitudinal axis from a primary air and fuel injection system that defines a forward end, through an interface at which the combustor connects to the turbine, and through a row of stator blades in the turbine that defines an aft end; and a downstream injection system that includes two injection stages, a first stage and a second stage, that are axially spaced along the longitudinal axis of the interior flowpath. The first stage and the second stage each includes multiple injectors configured to inject an air and fuel mixture into the interior flowpath.
    Type: Application
    Filed: March 15, 2013
    Publication date: September 18, 2014
    Inventors: Lewis Berkley Davis, JR., Krishna Kumar Venkataraman, Kaitlin Marie Graham
  • Publication number: 20140260261
    Abstract: A turbomachine is provided and includes a combustor in which fuel and air are combusted, a turbine disposed for reception of products of combustion from the combustor, a transition piece fluidly interposed between the combustor and the turbine and including a body formed to define dilution holes configured to allow air to enter the combustor and for enabling steam injection toward a main flow of the products of the combustion proceeding from the combustor to the turbine and a fuel injection system supportively coupled to the transition piece and configured to inject fuel toward the main flow of the products of the combustion to thereby restore a flame temperature of the main flow of the products of the combustion reduced by steam injection enabled by the dilution holes.
    Type: Application
    Filed: March 13, 2013
    Publication date: September 18, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Carey Edward Romoser, Derrick Walter Simons
  • Publication number: 20140260309
    Abstract: A system includes a gas turbine engine having a combustor, and a fuel blending system. The fuel blending system further includes a first fuel supply configured to supply a first fuel, a second fuel supply configured to supply a second fuel, a first fuel circuit, a second fuel circuit, and a controller. The first fuel circuit may be configured to blend the first fuel and the second fuel to form a first fuel mixture. The second fuel circuit may be configured to blend the first fuel and the second fuel to form a second fuel mixture. The controller may be configured to regulate blending of the first fuel mixture and the second fuel mixture based on a measured composition of the first fuel.
    Type: Application
    Filed: March 15, 2013
    Publication date: September 18, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Arvind Venugopal Menon, Alan Meier Truesdale, Abhijit Prabhakar Kulkarni, Predrag Popovic
  • Publication number: 20140260264
    Abstract: A system for controlling air flow rate of a compressed working fluid to a fuel injector of a combustor includes an outer casing that defines a high pressure plenum around a portion of the combustor, an extraction port in fluid communication with the high pressure plenum and an inlet port. The combustor includes a plurality of fuel injectors arranged around a combustion liner, an inner flow sleeve, an outer air shield that surrounds the plurality of fuel injectors and the inner flow sleeve. The outer air shield defines an injection an air plenum between the outer air shield and the inner flow sleeve and an inlet to the injection air plenum. An external fluid circuit provides fluid communication between the extraction port and the inlet port. A baffle extends between the outer casing and the outer air shield to provide flow separation between the inlet and the high pressure plenum.
    Type: Application
    Filed: March 18, 2013
    Publication date: September 18, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Lucas John Stoia, Patrick Benedict Melton, Richard Martin DiCintio
  • Publication number: 20140260265
    Abstract: A combustion chamber (10, 20) for a gas turbine (1) with at least two combustion zones (23, 24) and at least one burner arrangement (11, 28) for the combustion of a fuel/air mixture in the combustion zones (23, 24). The burner arrangement (11, 28) has at least one premixing passage (29) that opens into the combustion zones (23, 24) to provide a fuel/air mixture, and an air supply (32) and at least one fuel supply (33) encompassed in the burner arrangement (11, 28) and open into the premixing passage (29). The combustion chamber permits a particularly effective damping of combustion chamber pressure fluctuations. To this end, the air supply (32) is designed in a stepped manner such that the outlet openings (34, 34a, 34b, 34c) of the stepped air supply that open into the premixing passage can be assigned different delay times (?1, ?2, ?3), which damps the fluctuations.
    Type: Application
    Filed: October 19, 2012
    Publication date: September 18, 2014
    Applicant: Seimens Aktiengesellschaft
    Inventors: Christian Beck, Olga Deiss, Werner Krebs, Bernhard Wegner
  • Publication number: 20140260263
    Abstract: One embodiment of the present invention is a turbine nozzle segment for a turbine section of a gas turbine. The turbine nozzle segment includes an inner platform, an outer platform and an airfoil that extends therebetween. The airfoil includes a forward portion and an aft portion that is disposed downstream from the forward portion. The turbine nozzle segment further includes a fuel injection insert that extends between the inner platform and the outer platform downstream from the aft portion of the airfoil. The fuel injection insert includes a fuel circuit that extends within the fuel injection insert, and a plurality of fuel injection ports disposed within the fuel injection insert. The plurality of fuel injection ports provide for fluid communication with the fuel circuit.
    Type: Application
    Filed: March 18, 2013
    Publication date: September 18, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventor: Thomas Raymond Farrell
  • Publication number: 20140260304
    Abstract: A method including providing a wet algae material having been subjected to a refinement process without a water separation phase; supplying the wet algae material including a water fraction and an algae-grown biofuel to a turbine engine; and operating the turbine engine with the wet algae material where a retained portion of the water fraction is retained in the wet biofuel during a manufacturing process not including a dehydration step and includes an amount sufficient to reduce generation of a quantity of nitrogen oxides, and where the turbine engine can further include a combustor capable of combusting the wet biofuel.
    Type: Application
    Filed: December 27, 2013
    Publication date: September 18, 2014
    Applicant: ROLLS-ROYCE CORPORATION
    Inventors: William G. CUMMINGS, III, Enrico LO GATTO
  • Patent number: 8826665
    Abstract: An example gas turbine engine hose arrangement includes a hose configured to communicate fluid and a thermal blanket directly adjacent the hose. A section of the hose is radially closer to a centerline of the gas turbine engine than the thermal blanket. An example method of limiting hose exposure to thermal energy includes routing a hose near a combustor housing of a gas turbine engine and covering the hose with thermal blanket to limit thermal energy communicated radially inwardly toward an axial center of the combustor housing.
    Type: Grant
    Filed: September 30, 2009
    Date of Patent: September 9, 2014
    Assignee: Hamilton Sunstrand Corporation
    Inventor: Eric Andrew Nager
  • Publication number: 20140245739
    Abstract: A method for purging fuel from a fuel system of a gas turbine engine on shutdown of the engine comprises, in one aspect, terminating a fuel supply to the fuel system and using the residual compressed air to create a reversed pressure differential in the fuel system relative to a forward pressure differential of the fuel system used to maintain fuel supply for engine operation, and under the reversed pressure differential substantially purging the fuel remaining in the system therefrom to a fuel source.
    Type: Application
    Filed: May 15, 2014
    Publication date: September 4, 2014
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventor: Kevin Allan DOOLEY
  • Patent number: 8820087
    Abstract: A method and system for controlling delivery of fuel to a dual stage nozzle in the combustor of a gas turbine. A liquid fuel is conveyed from a single stage fuel supply through a plurality of primary fuel supply lines to a first nozzle stage including a plurality of primary nozzles. A predetermined operating condition of the gas turbine is identified and a signal is produced in response to the identified operating condition. The signal effects actuation of valves located on secondary fuel supply lines extending from each of the primary fuel supply lines to supply fuel to respective secondary nozzles.
    Type: Grant
    Filed: September 8, 2008
    Date of Patent: September 2, 2014
    Assignee: Siemens Energy, Inc.
    Inventor: William R. Ryan
  • Patent number: 8820086
    Abstract: An endcover assembly for a turbine combustor adapted to support one or more combustor nozzles includes a substantially flat plate having one side which in use, faces a combustion chamber and an opposite side which, in use, faces away from the combustion chamber. At least one fuel passage extends through the substantially flat plate. A fuel manifold porting block is secured to the opposite side of the flat plate with at least one port aligned with the at least one passage. A fuel restrictor insert formed with multiple flow orifices is located between the flat plate and the fuel manifold porting block in alignment with the at least one fuel passage and the at least one port.
    Type: Grant
    Filed: January 18, 2011
    Date of Patent: September 2, 2014
    Assignee: General Electric Company
    Inventors: Donald Mark Bailey, Donald Timothy Lemon, Kwanwoo Kim, Patrick Benedict Melton
  • Publication number: 20140238037
    Abstract: One embodiment of the present disclosure is a unique method for operating a gas turbine engine during flight operation of the gas turbine engine in an aircraft. Another embodiment of the present disclosure is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines. 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: December 20, 2013
    Publication date: August 28, 2014
    Applicant: Rolls-Royce Corporation
    Inventor: William G. Cummings, III
  • Patent number: 8813470
    Abstract: In a method for operating a fuel supply for a heat engine, in a first step the block valve (4) and the control valve (5) are closed, with the vent valve (7) closed. In a second step, the vent valve (7) is opened so that fuel volume (V1) which is present in the fuel line section (1?) and vent line (6?) can drain. In a third step, the vent valve (7) is closed. In a fourth step, the control valve (5) is opened. In a fifth step, the fuel volume (V1) is replenished by a pressure-driven backflow of fuel from the combustion process (3). In a sixth step, the control valve (5) is closed and then the vent valve (7) is opened, for draining of the replenished fuel volume (V1) which has been formed there on account of the action taken according to the fifth step.
    Type: Grant
    Filed: June 15, 2012
    Date of Patent: August 26, 2014
    Assignee: Alstom Technology Ltd.
    Inventor: Hermann Engesser
  • Patent number: 8813504
    Abstract: A protocol for assembling a fuel shut off pin valve assembly for a gas turbine engine. The protocol outlines a specific sequence of events in order to ensure failsafe incorporation of a fuel shut off valve assembly within the low pressure turbine area and specifically within the engine casing of the gas turbine.
    Type: Grant
    Filed: September 30, 2010
    Date of Patent: August 26, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Guy Lefebvre, Claude Giardetti
  • Publication number: 20140230449
    Abstract: A valve control device is provided in a gas turbine having a combustor for generating combustion gas, a turbine driven by the combustion gas generated by the combustor, a flow rate regulating valve for regulating the flow rate of the fuel to be supplied to the combustor, and a pressure regulating valve disposed upstream of the flow rate regulating valve, for regulating the fuel pressure. The valve control device controls the opening degree of the valve. The valve control device includes a load decrease detection part which detects a load decrease of the gas turbine, and a pressure control part which controls the opening degree of the valve in accordance with the output of the gas turbine. The valve control device suppresses instability of the gas turbine output even when the load rapidly decreases.
    Type: Application
    Filed: November 22, 2012
    Publication date: August 21, 2014
    Applicant: Mitsubishi Hitachi Power Systems, Ltd.
    Inventors: Akihiko Saito, Takashi Sonoda, Takafumi Uda, Fuminori Fujii
  • Publication number: 20140216037
    Abstract: An engine fuel control system includes a metering valve to control fuel flow between the supply and delivery line with a pressure drop control regulating the pressure across the valve and maintain a substantially constant pressure across the valve. The fuel control system includes a backup system controllable by a pullback signal to operate the pressure control, thus increasing the pullback signal reducing the fuel flow between the supply and delivery line. The fuel control system detects a start of an engine overthrust event, and when the upward runaway is caused by the arrested overthrust event. The fuel control system's controller which (i) determines the overthrust detection, the pullback signal increase rate and the pullback signal offset, (ii) sends the pullback signal to the backup system at the rate of increase, and (iii), reduces the pullback signal to the backup system when the upward runaway is arrested by the offset.
    Type: Application
    Filed: January 14, 2014
    Publication date: August 7, 2014
    Applicant: ROLLS-ROYCE CONTROLS AND DATA SERVICES LIMITED
    Inventors: Alexander MACDONALD, Mohammad Khalid KHAN, Nigel Herbert HENSON
  • Patent number: 8793971
    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: Grant
    Filed: May 25, 2010
    Date of Patent: August 5, 2014
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Gerald P. Dyer, Kevin Gibbons
  • Patent number: 8789353
    Abstract: A fuel system comprises a first, variable displacement fuel pump operable to supply fuel through a metering valve to an engine, a control servo operable to control the operation of the first pump, a pressure drop control valve (PDCV) responsive to a pressure drop across the metering valve, a second fuel pump, and a spill valve movable between an open position in which substantially all of the fuel supplied by the second fuel pump is returned to an inlet side thereof, and a closed position, or partially closed position, wherein a proportion of the fuel supplied by the second pump is delivered to the engine.
    Type: Grant
    Filed: March 12, 2008
    Date of Patent: July 29, 2014
    Assignee: Goodrich Control Systems
    Inventor: Daniel James Bickley
  • Patent number: 8783040
    Abstract: A fuel delivery system for a combustion turbine engine, comprising: a fuel line having a fuel compressor and parallel branches downstream of the fuel compressor: a cold branch that includes an after-cooler; and a hot branch that bypasses the after-cooler; a rapid heating value meter configured to measure the heating value of the fuel from the fuel source and transmit heating value data relating to the measurements; means for controlling the amount of fuel being directed through the cold branch and the amount of fuel being directed through the hot branch; and a fuel-mixing junction at which the cold branch and the hot branch converge; wherein the fuel-mixing junction resides in close proximity to a combustor gas control valve.
    Type: Grant
    Filed: February 25, 2010
    Date of Patent: July 22, 2014
    Assignee: General Electric Company
    Inventors: Dean Matthew Erickson, Timothy Russell Bilton
  • Publication number: 20140196459
    Abstract: A gas turbine engine fuel supply system includes a primary gear pump, a secondary gear pump, and a pump bypass valve. The primary gear pump always actively delivers fuel to the downstream fuel system, and is sized to supply 100% of the burn flow needed at a select low demand condition. The secondary gear pump is sized to make up the remainder of the flow at high demand conditions, and actively delivers fuel to the downstream fuel system only during those conditions. To supply discharge fuel pressures in excess of gear pump capability, a supercharger pump is disposed upstream of the primary and secondary gear pumps. The pump bypass valve is configured to regulate fuel pressure at the primary gear pump outlet to one of a plurality of preset differential pressures above one of a plurality of fuel load pressures and prevents reverse pressurization of the gear pumps.
    Type: Application
    Filed: March 14, 2013
    Publication date: July 17, 2014
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Paul W. Futa, Edward Zielinski, Larry Portolese, David Tuttle
  • Publication number: 20140196463
    Abstract: A gas turbine engine fuel supply system includes a primary gear pump and a secondary gear pump. The primary gear pump always actively delivers fuel to the downstream fuel system, and is sized to supply 100% of the burn flow needed at a select low demand condition. The secondary gear pump is sized to make up the remainder of the flow at high demand conditions, and actively delivers fuel to the downstream fuel system only during those conditions. To supply discharge fuel pressures in excess of gear pump capability, a supercharger pump is disposed upstream of the primary and secondary gear pumps. The supercharger pump is preferably activated only during high demand conditions as an additional energy conservation measure.
    Type: Application
    Filed: March 14, 2013
    Publication date: July 17, 2014
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Edward Zielinski, Paul W. Futa, David Tuttle
  • Publication number: 20140196466
    Abstract: Methods and systems for operating a gas turbine engine including a fuel delivery system and a plurality of combustor assemblies are provided. The fuel delivery system comprises a primary fuel circuit configured to continuously supply fuel to each of the plurality of combustor assemblies during a first mode of operation and a second mode of operation. At least one secondary fuel circuit of the fuel delivery system is configured to supply fuel to each of the plurality of combustor assemblies during the second mode of operation. The secondary fuel circuit includes at least one isolation valve coupled in flow communication with each of the plurality of combustor assemblies. The at least one isolation valve facilitates preventing fluid flow upstream into the secondary fuel circuit during the first mode of operation. The fuel delivery system, using the isolation valve, replaces a purging system in the gas turbine engine.
    Type: Application
    Filed: January 15, 2013
    Publication date: July 17, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Fabien Thibault Codron, John Edward Pritchard, Stanley Kevin Widener
  • Patent number: 8769954
    Abstract: A fluid manifold apparatus includes: (a) an array of spaced-apart manifold fittings, each manifold fitting aligned in a predetermined angular orientation. Each manifold fitting includes: (i) a tubular neck; (ii) a pair of spaced-apart tubular arms extending away from a first end of the neck; and (iii) a coupling connected to a second end of the neck; and (b) a plurality of curved tubes, each tube being coupled to one arm of each of two adjacent manifold fittings.
    Type: Grant
    Filed: December 31, 2009
    Date of Patent: July 8, 2014
    Assignee: General Electric Company
    Inventors: Kevin Michael Fiebig, Joshua Brown, Joseph Nath
  • Publication number: 20140165571
    Abstract: A fuel circuit for a turbine engine, the fuel circuit comprising: 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: Application
    Filed: December 17, 2013
    Publication date: June 19, 2014
    Applicant: SNECMA
    Inventors: Philippe VERTENOEUIL, Gilles BRUN
  • Publication number: 20140165579
    Abstract: The speed of a high-pressure turbine of a gas turbine engine may be determined using known centrifugal pump affinity relationships for a fuel pressure apparatus, fuel pressure apparatus input and output pressures, and gear ratios for a mechanical linkage between the high-pressure turbine and the fuel pressure apparatus. The technique avoids wear-related variations in gas pressure based measurements and also applies to fuel pressure apparatus using both single pump and multiple pump configurations.
    Type: Application
    Filed: December 18, 2012
    Publication date: June 19, 2014
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventor: Tyler J. Selstad
  • Publication number: 20140165576
    Abstract: It is desirable for a gas turbine system to operate in a wide range operating conditions. However, under certain conditions there exist dynamic boundaries that limit a combustor from reaching its designated condition. Perturbation devices formed of electromagnetic plates can be incorporated into fuel nozzles of the combustor to influence the dynamics so that the range of operating conditions can be widened. The perturbation devices vibrate according to the perturbation signals provided from a dynamics controller. The vibration characteristics of the perturbation devices can be controlled by controlling the attributes of the perturbation signals. The vibrations influence the dynamics of fluid—fuel, oxidant, or both—flowing past the perturbation devices within the fuel nozzles.
    Type: Application
    Filed: December 13, 2012
    Publication date: June 19, 2014
    Applicant: General Electric Company
    Inventors: Wei CHEN, Keith McManus, John Lipinski, Carolyn Antoniono
  • Publication number: 20140165587
    Abstract: A system for converting gaseous fuel into liquid fuel is provided. The system may have a combustor configured to receive a supply of gaseous fuel. The system may also have a gas compressor configured to direct gaseous fuel from the supply into the combustor. The system may also have an air compressor configured to direct compressed air into the combustor, and a turbine in fluid communication with an outlet of the combustor. The turbine may be connected to drive the gas compressor and the air compressor. The system may also have at least one heat exchanger in fluid communication with an outlet of the gas compressor and an outlet of the air compressor. The system may also have at least one expander in fluid communication with an outlet of the at least one heat exchanger. The system may also have a condenser in fluid communication with an outlet of the at least one expander.
    Type: Application
    Filed: December 14, 2012
    Publication date: June 19, 2014
    Inventor: Aaron Foege
  • Publication number: 20140165580
    Abstract: A fuel routing system of a gas turbine engine includes a primary fuel circuit in communication with a fuel source and a fuel distribution manifold. Also included is a secondary fuel circuit extending from the primary fuel circuit to a plurality of fuel nozzles configured to direct fuel to a plurality of combustor chambers. Further included is a main fuel flow control valve disposed in the primary fuel circuit for restricting a fuel flow to the fuel distribution manifold upon removal of an electrical load operably coupled to the gas turbine engine. Yet further included is a plurality of check valves disposed between the secondary fuel circuit and the primary fuel circuit for restricting the fuel flow between the secondary fuel circuit and the primary fuel circuit.
    Type: Application
    Filed: December 18, 2012
    Publication date: June 19, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: James Arthur Simmons, William Randolph Shinkle
  • Patent number: 8752386
    Abstract: A fuel injector for use in a gas turbine engine combustor assembly. The fuel injector includes a main body and a fuel supply structure. The main body has an inlet end and an outlet end and defines a longitudinal axis extending between the outlet and inlet ends. The main body comprises a plurality of air/fuel passages extending therethrough, each air/fuel passage including an inlet that receives air from a source of air and an outlet. The fuel supply structure communicates with and supplies fuel to the air/fuel passages for providing an air/fuel mixture within each air/fuel passage. The air/fuel mixtures exit the main body through respective air/fuel passage outlets.
    Type: Grant
    Filed: May 25, 2010
    Date of Patent: June 17, 2014
    Assignees: Siemens Energy, Inc., Mikro Systems, Inc.
    Inventors: Timothy A. Fox, Reinhard Schilp, Domenico Gambacorta
  • Patent number: 8752387
    Abstract: Fuel control arrangements for gas turbine engines generally comprise an injector and a fuel control valve. Typically the fuel control valve is controlled in terms of fuel demand through fuel pressure presented to the valve. Fuel demand may vary and in such circumstances stagnation of fuel adjacent to the valve may cause degradation of the fuel and therefore spurious operational performance. By providing a dedicated working fluid, and typically hydraulic, pressure to the valve a variable aperture port can be displaced to alter the fuel flow configuration within the valve. In such circumstances different fuel valve conditions can be generated by altering the available area of aperture in the port to divert or present fuel to the injector between and across first or primary fuel paths and second or pilot fuel paths as required. Thus more flexibility with regard to fuel presentation to the injector is achieved as well as consistency with respect to avoiding fuel degradation as fuel demand varies.
    Type: Grant
    Filed: May 21, 2009
    Date of Patent: June 17, 2014
    Assignee: Rolls-Royce PLC
    Inventor: Mark Scully
  • Publication number: 20140157780
    Abstract: A fuel control module for a gas turbine engine and method of installation. The fuel control module includes a first frame unit, a second frame unit, a fuel path, and a fuel controller components. The first frame unit and the second frame unit include features for installation in multiple installations and/or multiple configurations.
    Type: Application
    Filed: December 12, 2012
    Publication date: June 12, 2014
    Applicant: SOLAR TURBINES INCORPORATED
    Inventors: Darren Matthew Stratton, Gregory Lee Landrum
  • Publication number: 20140157785
    Abstract: A system includes a fuel supply system. The fuel supply includes a primary fuel supply, a fuel additive supply, and a common pipeline coupled to the primary fuel and fuel additive supplies. The primary fuel supply includes a primary fuel having a first average molecular weight. The fuel additive includes a fuel additive having a second molecular weight that is greater than the first average molecular weight. The common pipeline is configured to direct a mixture of the primary fuel and the fuel additive into a fuel nozzle.
    Type: Application
    Filed: December 6, 2012
    Publication date: June 12, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Mahesh Bathina, Madanmohan Manoharan
  • Publication number: 20140157786
    Abstract: A gas turbine system includes a gas turbine including a combustor for combusting a fuel and a control assembly configured to control at least one of a fuel system and the combusting of the combustor based on providing values corresponding to at least one of fuel characteristics and combustor characteristics to a fuel induction time transfer function.
    Type: Application
    Filed: December 7, 2012
    Publication date: June 12, 2014
    Applicant: General Electric Company
    Inventor: Roy Marshall Washam