Fuel Preheated Upstream Of Injector Patents (Class 60/736)
  • Patent number: 10859089
    Abstract: An integrated oil system manifold is provided, which includes a reverse rotation protection element, a main pump check valve, an auxiliary pump check valve, and a pressure relief valve, wherein the reverse rotation protection element, the main pump check valve, the auxiliary pump check valve, and the pressure relief valve are integrated with a housing of the integrated oil system manifold. Furthermore, a temperature control element, a filter, a heat exchanger, an integral main pump assembly, and an integral auxiliary pump assembly may also be included in the integrated manifold. An associated method is also provided.
    Type: Grant
    Filed: September 26, 2017
    Date of Patent: December 8, 2020
    Assignee: ATLAS COPCO COMPTEC LLC
    Inventors: Ross Morgan Snyder, Jeffrey Russell Whitehouse
  • Patent number: 10767485
    Abstract: A gas turbine engine is disclosed. The gas turbine engine includes a first rotor supporting a first plurality of circumferentially spaced rotor blades and a second rotor disposed axially downstream of the first rotor and supporting a second plurality of circumferentially spaced rotor blades, a first bore cavity between the first rotor and the second rotor, a first fluid passageway configured to provide cooled air to the first bore cavity and a first anti-vortex component positioned proximate the first bore cavity and configured to increase pressure of the cooled air as the cooled air traverses radially outward from the first bore cavity.
    Type: Grant
    Filed: January 8, 2018
    Date of Patent: September 8, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Matthew E Bintz, Enzo DiBenedetto, Paul E Coderre
  • Patent number: 10676206
    Abstract: A system and a method for detecting a failure of a heat exchanger provided on an engine of an aircraft. An out-of-range fuel temperature downstream of an outlet of the heat exchanger is detected. A health of a fuel tank temperature signal indicative of a temperature of at least one fuel tank of the aircraft is monitored. A main oil temperature signal indicative of a temperature of oil in the engine is received. The failure is detected based on the main oil temperature and on the health of the fuel tank temperature signal.
    Type: Grant
    Filed: December 8, 2017
    Date of Patent: June 9, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Patrick Manoukian, Robin Watt, Amandeep Chahal
  • Patent number: 10578023
    Abstract: Embodiments of the present disclosure include methods, systems and program products for controlling a water bath heater for a fuel gas. Methods according to the present disclosure can include: calculating at least one calculable condition of the fuel gas based on a set of conditions of the fuel gas entering the water bath heater and a type of control valve located downstream of the water bath heater; calculating a target temperature differential for the fuel gas based a set of conditions of the fuel gas entering the water bath heater and the at least one calculable condition; and adjusting an operating parameter of the water bath heater to adjust a temperature of the fuel gas leaving the water bath heater by the target temperature differential.
    Type: Grant
    Filed: April 25, 2017
    Date of Patent: March 3, 2020
    Assignee: General Electric Company
    Inventors: Hua Zhang, Dean Matthew Erickson
  • Patent number: 10465563
    Abstract: A gas turbine cooling system of the present invention includes a cooler that cools compressed air extracted from an air compressor to make cooling air, a cooling air compressor that supplies the cooling air to a combustion liner of a combustor, and an IGV that regulates a flow rate of the cooling air. The control device of the gas turbine cooling system includes a target value setting part that determines a target value with respect to a flow rate equivalent value of the cooling air according to detected temperature of the cooling air, a correction driving amount calculation part that obtains a correction driving amount which reduces a deviation of detected flow rate equivalent value of the cooling air with respect to the target value, and a drive command output part that outputs a drive command corresponding to the correction driving amount to the IGV.
    Type: Grant
    Filed: February 22, 2013
    Date of Patent: November 5, 2019
    Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.
    Inventor: Akihito Kunihiro
  • Patent number: 10330010
    Abstract: A compressor section for use in a gas turbine engine comprises a compressor rotor having a hub and a plurality of blades extending radially outwardly from the hub and an outer housing surrounding an outer periphery of the blades. A tap taps air at a radially outer first location, passing the tapped air through a heat exchanger, and returning the tapped air to an outlet at a second location which is radially inward of the first location, to provide cooling air adjacent to the hub. A gas turbine engine is also disclosed.
    Type: Grant
    Filed: December 14, 2015
    Date of Patent: June 25, 2019
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Brian D. Merry, Jesse M. Chandler, William K. Ackermann, Matthew R. Feulner, Om P. Sharma
  • Patent number: 10221768
    Abstract: A heat exchanger for use in high pressure environments, such as in a gas turbine engine, includes an outer casing, a tubular element within the outer casing and an inner sleeve within the tubular element. The tubular element has an outer surface and an inner surface. The outer casing and outer surface of the tubular element define a first annular passage through which a first fluid flow path extends. The inner sleeve and inner surface of the tubular element define a second annular passage through which a second fluid flow path extends. The first annular passage is sealed against the outer surface of the tubular element and the second annular passage is sealed within the inner surface of the tubular element.
    Type: Grant
    Filed: October 13, 2015
    Date of Patent: March 5, 2019
    Assignee: ROLLS-ROYCE plc
    Inventor: Michael John Agg
  • Patent number: 9470145
    Abstract: A system for heating fuel in a combined cycle gas turbine includes a fuel heat exchanger downstream from a turbine outlet, and the fuel heat exchanger has an exhaust gas inlet, an exhaust gas outlet, a fuel inlet, and a fuel outlet. A first exhaust gas plenum has a first exhaust gas inlet connection between the turbine outlet and a heat exchanger and a first exhaust gas outlet connection upstream from the exhaust gas inlet. A second exhaust gas plenum has a second exhaust gas inlet connection downstream from at least a portion of the heat exchanger and a second exhaust gas outlet connection upstream from the exhaust gas inlet.
    Type: Grant
    Filed: October 15, 2012
    Date of Patent: October 18, 2016
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: David Wesley Ball, Jr., Korey Frederic Rendo, Dean Matthew Erickson, Diego Fernando Rancruel, Leslie Yung-Min Tong
  • Patent number: 9435258
    Abstract: A system for heating combustor fuel includes a turbine exhaust plenum and a heat exchanger downstream from the turbine exhaust plenum. The heat exchanger has an exhaust inlet, an exhaust outlet, a fuel inlet, and a fuel outlet. An exhaust recirculation plenum has a recirculation inlet connection downstream from the exhaust outlet and a recirculation outlet connection upstream from the exhaust inlet. The system further includes structure for controlling a recirculated exhaust flow from the exhaust outlet into the exhaust recirculation plenum.
    Type: Grant
    Filed: October 15, 2012
    Date of Patent: September 6, 2016
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Durgaprasad Janapaneedi, Korey Frederic Rendo, Dean Matthew Erickson, Timothy Russell Bilton, Christina Renee Pompey
  • Patent number: 9291351
    Abstract: A combustion chamber including a first fuel injector and a second fuel injector, the first and second fuel injectors being arranged to inject fuel into a mainstream flow of air with the second fuel injector arranged downstream of the first fuel injector. A method of mixing fuel and air in a combustion chamber, including injecting fuel into a mainstream flow of air with a first fuel injector; injecting fuel into the mainstream flow of air with a second fuel injector, which is arranged downstream of the first fuel injector; injecting fuel into the mainstream flow with the first fuel injector such that the resulting mixture between the first and second fuel injectors has an equivalence ratio less than the lean flame stability limit; and injecting fuel into the mainstream flow with the second fuel injector such that a combustion zone is provided downstream of the second fuel injector.
    Type: Grant
    Filed: June 12, 2012
    Date of Patent: March 22, 2016
    Assignee: ROLLS-ROYCE plc
    Inventor: Stephen C. Harding
  • Patent number: 9279346
    Abstract: Certain embodiments of the invention may include systems, methods, and apparatus for determining online stress and life consumption of a heat recovery steam generator (HRSG). According to an example embodiment of the invention, a method for assessing components of a HRSG is provided. The method includes receiving HRSG design parameters; determining thermal stress data associated with the one or more HRSG components based at least in part on one or more historical, real-time, or calculated temperature sensor data associated with the one or more HRSG components; and determining cycle-related life consumption data associated with the one or more HRSG components based at least in part on the HRSG design parameters and the determined thermal stress data.
    Type: Grant
    Filed: June 25, 2012
    Date of Patent: March 8, 2016
    Assignee: General Electric Company
    Inventors: William B. Julian, Ashok D. Acharya, Joel Donnell Holt, Robert John Gdaniec
  • Patent number: 9261279
    Abstract: A gas/liquid fuel nozzle assembly includes a premixing tube bundle having an array of mixing tubes, a fuel plenum delivering fuel to the mixing tubes, a cartridge tube disposed within the fuel plenum, and a liquid fuel cartridge disposed in the cartridge tube. The liquid fuel cartridge is spaced from the cartridge tube to define an annulus. The cartridge tube and the fuel plenum are constructed in fluid communication such that gas fuel in the plenum is injected into the annulus.
    Type: Grant
    Filed: May 25, 2012
    Date of Patent: February 16, 2016
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: James Harold Westmoreland, Gregory Allen Boardman, Patrick Benedict Melton
  • Patent number: 9074773
    Abstract: A combustor assembly is disclosed. The combustor assembly may include an annular trapped vortex cavity located adjacent to a downstream end of a bundle of air/fuel premixing injection tubes. The annular trapped vortex cavity may include an opening at a radially inner portion of the annular trapped vortex cavity adjacent to the head end of the bundle of premixing tubes. The annular trapped vortex cavity may also include one or more air injection holes and one or more fuel sources disposed about the annular trapped vortex cavity such that the one or more air injection holes and the one or more fuel sources are configured to drive a vortex within the annular trapped vortex cavity.
    Type: Grant
    Filed: February 7, 2012
    Date of Patent: July 7, 2015
    Assignee: General Electric Company
    Inventors: Gregory Allen Boardman, Ronald Chila, Johnie F. McConnaughhay
  • Patent number: 9051056
    Abstract: A fuel heat management system including a fuel line for conveying fuel, and a fuel/oil heat exchanger which receives fuel flowing through the fuel line. The fuel heat management system further comprises an oil line for circulating oil from an engine oil system to the fuel/oil heat exchanger and back to the engine oil system. The fuel/oil heat exchanger brings the oil and the fuel into heat exchange relationship. The fuel heat management system further includes an air/oil heat exchanger which receives oil flowing through the oil line, the air/oil heat exchanger bringing the oil and air into heat exchange relationship. The fuel heat management system further includes an air/fuel heat exchanger which receives fuel flowing through the fuel line, the air/fuel heat exchanger bringing the fuel and air into heat exchange relationship.
    Type: Grant
    Filed: March 2, 2011
    Date of Patent: June 9, 2015
    Assignee: ROLLS-ROYCE plc
    Inventor: Robert E. Leese
  • Publication number: 20150107254
    Abstract: A closed circuit fuel heating system is provided for heating at least two types of fuel. The heating system includes a heat transfer subsystem disposed in a gas turbine system exhaust. A first heat exchange subsystem is coupled to a first fuel source and the heat transfer subsystem. The first heat exchange subsystem is provided with a control component for controlling a flow of a working fluid through the first heat exchange subsystem. A second heat exchange subsystem may be coupled to a second fuel source and the heat transfer subsystem. The second heat exchange subsystem is provided with a control component for controlling a flow of the working fluid through the second exchange subsystem. A subsystem for controlling the temperature of the working fluid is also provided.
    Type: Application
    Filed: October 23, 2013
    Publication date: April 23, 2015
    Applicant: General Electric Company
    Inventors: Jason Brian Shaffer, Alston Ilford Scipio, Sanji Ekanayake, Jean-Marc Carré, Paul Robert Fernandez
  • 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: 8943827
    Abstract: A gas turbine engine with a fuel air heat exchanger located in the high pressure plenum. The heat exchanger includes at least one air conduit and at least one fuel conduit in heat exchange relationship with one another, with a fuel flow communication between a fuel source and fuel distribution members of the combustor being provided at least partly through the at least one fuel conduit, and the at least one air conduit defining a fluid flow communication between the high pressure plenum and an engine component to be cooled by the compressed air.
    Type: Grant
    Filed: May 31, 2011
    Date of Patent: February 3, 2015
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Lev Alexander Prociw, Eduardo Hawie
  • Patent number: 8938966
    Abstract: A device and a method for using overcapacities in the power grid is provided. In case of an oversupply of energy, the energy is transferred to a thermal storage device directly via a heating element and in the discharge case of the thermal storage device the heat is removed from the thermal storage device and made available to a thermodynamic cycle whereby electrical energy is produced. The heat from the thermal storage device is used to preheat air in an air feed line to a combustion chamber, or fuel is pre-heated using heat from the thermal storage device.
    Type: Grant
    Filed: March 5, 2009
    Date of Patent: January 27, 2015
    Assignee: Siemens Aktiengesellschaft
    Inventors: Tobias Jockenhoevel, Norbert König, Rainer Nies, Nicolas Vortmeyer, Erik Wolf
  • Patent number: 8931279
    Abstract: A switchable solar heating device for a gas turbine with a compressor, having a valve for electively bypassing a solar heater arranged between a compressor stage and a turbine stage of the gas turbine. The valve is constructed as a 4-way valve with a compressor port that can be connected to the compressor stage, a turbine port that can be connected to the turbine stage, a solar input port that can be connected to an input of the solar heater, and a solar output port that can be connected to an output of the solar heater.
    Type: Grant
    Filed: October 23, 2009
    Date of Patent: January 13, 2015
    Assignee: Man Diesel & Turbo SE
    Inventor: Hans-Otto Jeske
  • Publication number: 20150000298
    Abstract: Advanced gas turbines and associated components, systems and methods are disclosed herein. A gas turbine configured in accordance with a particular embodiment includes a rotor operably coupled to a shaft and a stator positioned adjacent to the rotor. A coolant line extends at least partially through the stator to transfer heat out of an air flow within a compressor section of the gas turbine.
    Type: Application
    Filed: December 20, 2013
    Publication date: January 1, 2015
    Applicant: ADVANCED GREEN TECHNOLOGIES, LLC
    Inventor: Roy Edward McAlister
  • Patent number: 8899009
    Abstract: A heat exchanger has a first passage to be connected to a source of fuel. The heat exchanger has an outlet to communicate the fuel downstream. A second passage connects to a source of air. The air passes adjacent to the first passage to heat fuel in the first passage. A jet pump is positioned downstream of the second passage to receive air from the second passage. The jet pump includes a tap connected to a housing compartment to drain fluid from the compartment. A method is also disclosed.
    Type: Grant
    Filed: January 5, 2011
    Date of Patent: December 2, 2014
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Jay M. Francisco, Greg R. Giddings
  • Patent number: 8899047
    Abstract: Provided is a power plant including a gas turbine that uses a fuel gas as a fuel; a fuel gas cooler that cools the fuel gas, which is to be pressurized in a fuel gas compressor and re-circulated, using cooling water; and a dust collection device that separates/removes impurities from the fuel gas that is to be guided to the fuel gas compressor; wherein the power plant further includes heating means that heats the fuel gas that is to be guided to the dust collection device using the fuel gas that has been used to generate an anti-thrust force acting on a rotor of the fuel gas compressor.
    Type: Grant
    Filed: June 20, 2011
    Date of Patent: December 2, 2014
    Assignee: Mitsubishi Heavy Industries, Ltd.
    Inventors: Hiroshi Tanabe, Eiki Anzawa
  • Patent number: 8893468
    Abstract: Fuel is oxidized with air in a pressurized reaction chamber containing water. Water, fuel, or both may be communicated into the reaction chamber in a gaseous state, a liquid state, or both. For example, a liquid mixture that includes the water and/or the fuel can be evaporated to form a gas mixture, and the gas mixture can be communicated into the reaction chamber. Additionally or alternatively, the liquid mixture that includes the water and/or the fuel can be communicated into the reaction chamber and evaporated in the reaction chamber. The water and the fuel may be communicated into the reaction chamber separately or in combination.
    Type: Grant
    Filed: March 15, 2011
    Date of Patent: November 25, 2014
    Assignee: Ener-Core Power, Inc.
    Inventor: Edan D. Prabhu
  • Patent number: 8893466
    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: Grant
    Filed: March 18, 2011
    Date of Patent: November 25, 2014
    Assignee: Hamilton Sundstrand Corporation
    Inventor: Charles E. Reuter
  • Patent number: 8881530
    Abstract: A system may include an insulated water tank configured to store a first heated water from a first plant component during operation of a plant, and a fuel heater comprising a heat exchanger, wherein the heat exchanger is configured to transfer heat from the first heated water to a fuel for a gas turbine engine during startup of the plant.
    Type: Grant
    Filed: September 2, 2010
    Date of Patent: November 11, 2014
    Assignee: General Electric Company
    Inventors: Seyfettin Can Gulen, Tailai Hu
  • Patent number: 8858223
    Abstract: A Glycerin Fueled Afterburning Engine utilizes the power generation unit exhaust heat to pre-heat the glycerin, or similar difficult to combust fuel, and then utilizes regenerative burner heating to fully vaporize and superheat the fuel above the auto ignition temperature. The combustion inlet air is also highly preheated by the recuperative power generation cycle. The actual combustion process is then accomplished by hypergolic ignition from mixing the hot vapor with the hot air. The overall engine process operates on a cycle of (1) air compression, (2) indirect heating of air in an air heater, (3) air expansion, (4) air heating by combustion, and (5) air cooling by heat transfer to the incoming compressed air charge in the recuperator.
    Type: Grant
    Filed: September 21, 2010
    Date of Patent: October 14, 2014
    Assignee: Proe Power Systems, LLC
    Inventor: Richard Alan Proeschel
  • Publication number: 20140298817
    Abstract: A preparation of liquid fuel for combustion, particularly for ignition, in the burners of a gas turbine is proposed. A source of heated liquid fuel, particularly heated pressurized fuel, is arranged in a reservoir. The reservoir is arranged in parallel with a main fuel feed of a combustion system. The reservoir can be filled by the main fuel feed and/or evacuated into the main fuel feed. The reservoir contains a heating means, which heat the liquid fuel filled in the reservoir, particularly while circulating in the reservoir.
    Type: Application
    Filed: January 25, 2012
    Publication date: October 9, 2014
    Inventor: Andrew Shepherd
  • 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
  • Publication number: 20140260313
    Abstract: A micro-mixer/combustor to mix fuel and oxidant streams into combustible mixtures where flames resulting from combustion of the mixture can be sustained inside its combustion chamber is provided. The present design is particularly suitable for diffusion flames. In various aspects the present design mixes the fuel and oxidant streams prior to entering a combustion chamber. The combustion chamber is designed to prevent excess pressure to build up within the combustion chamber, which build up can cause instabilities in the flame. A restriction in the inlet to the combustion chamber from the mixing chamber forces the incoming streams to converge while introducing minor pressure drop. In one or more aspects, heat from combustion products exhausted from the combustion chamber may be used to provide heat to at least one of fuel passing through the fuel inlet channel, oxidant passing through the oxidant inlet channel, the mixing chamber, or the combustion chamber.
    Type: Application
    Filed: March 11, 2014
    Publication date: September 18, 2014
    Inventors: Jihad A. Badra, Assaad R. Masri
  • Patent number: 8820085
    Abstract: Provided is a lean fuel sucking gas turbine system including a compressor for compressing a mixed gas having a fuel and air mixed to a concentration of an inflammable limit or lower, thereby producing a compressed gas, a first catalyst combustor for burning the compressed gas by a catalyst reaction, a turbine adapted to be driven by a combustion gas from a second catalyst combustor, and a reproducer for heating the compressed gas to be introduced into the first catalyst combustor with an exhaust gas from the turbine. Between the turbine and the reproducer, there is arranged a duct burner for flame-burning a first auxiliary fuel in the exhaust gas. Thus, it is possible to attain efficient operation of the system while simplifying the entire constitution and to prevent the blow-by of the mixed gas.
    Type: Grant
    Filed: June 10, 2009
    Date of Patent: September 2, 2014
    Assignee: Kawasaki Jukogyo Kabushiki Kaisha
    Inventor: Shinichi Kajita
  • Publication number: 20140238041
    Abstract: The present application provides a fuel delivery system for a combustor with reduced coherence and/or reduced combustion dynamics. The combustor can assembly may include a first manifold for delivering a first flow of fuel to a first set of fuel injectors and a second manifold for delivering a second flow of fuel to a second set of fuel injectors. The first flow of fuel may have a first temperature and the second flow of fuel may have a second temperature. The first temperature may be higher than the second temperature.
    Type: Application
    Filed: February 27, 2013
    Publication date: August 28, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: SARAH LORI CROTHERS, CHRISTAN XAVIER STEVENSON, DAVID LEACH
  • Patent number: 8813471
    Abstract: Embodiments of the present invention may provide to a gas turbine a fuel gas saturated with water heated by a fuel moisturizer, which receives heat form a flash tank. A heat source for the flash tank may originate at a heat recovery steam generator. The increased mass flow associated with the saturated fuel gas may result in increased power output from the associated power plant. The fuel gas saturation is followed by superheating the fuel, preferably with bottom cycle heat sources, resulting in a larger thermal efficiency gain.
    Type: Grant
    Filed: June 29, 2011
    Date of Patent: August 26, 2014
    Assignee: General Electric Company
    Inventors: Seyfettin Can Gulen, Jatila Ranasinghe
  • Patent number: 8814958
    Abstract: A liquid fuel includes a hydrocarbon-based liquid fuel and an additive mixed with the hydrocarbon-based liquid fuel. The additive includes an endothermic fuel-cracking catalyst.
    Type: Grant
    Filed: July 22, 2011
    Date of Patent: August 26, 2014
    Assignee: United Technologies Corporation
    Inventor: He Huang
  • Patent number: 8763363
    Abstract: A method of assembling a turbine engine is provided. The method includes providing a heat exchanger having a curvilinear body. The method also includes coupling the heat exchanger to at least one of a fan casing and an engine casing of the turbine engine. The curvilinear body facilitates reducing pressure losses in airflow channeled into the heat exchanger.
    Type: Grant
    Filed: July 6, 2007
    Date of Patent: July 1, 2014
    Assignee: General Electric Company
    Inventor: Srikanth Ranganathan
  • Publication number: 20140165572
    Abstract: Thermal energy storage containing thermal energy extracted from a bottom cycle heat engine is leveraged to heat fuel gas supplied to a gas turbine engine operating in a top cycle heat engine. Further, an extracted portion of a working fluid generated in a steam generation source of the bottom cycle heat engine can be used along with the thermal energy storage to heat fuel gas.
    Type: Application
    Filed: December 14, 2012
    Publication date: June 19, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Raymond Pang, Kamlesh Mundra
  • Patent number: 8739550
    Abstract: The present invention provides a combustor for an aerospace gas turbine engine comprising two stages wherein each stage defines an inlet and an exit. The second stage inlet is in fluid communication with the first stage exit such that a first flowpath is defined and it passes substantially through the second stage. A plurality of flow channel tubes is positioned within the second stage and each flow channel tube passes sealingly through a header plate positioned upstream of the second stage inlet thereby defining a second flowpath that also passes substantially through the second stage. The first flowpath exit and the second flowpath exit are positioned adjacent and proximate to one another to provide for the generation of microflames or microflame jets exiting the second stage from between and around the flow channel tube exits. The first stage of the combustor provides a gasifier and a reformer.
    Type: Grant
    Filed: September 30, 2010
    Date of Patent: June 3, 2014
    Assignee: Precision Combustion, Inc.
    Inventors: Shahrokh Etemad, Benjamin D. Baird, Subir Roychoudhury, William C. Pfefferle
  • Publication number: 20140130478
    Abstract: A gas turbomachine includes a compressor portion, a turbine portion operatively connected to the compressor portion, a combustor assembly including at least one combustor fluidically connected to the turbine portion, and an accessory mechanically linked with and driven by the turbine portion. The gas turbomachine also includes a fuel pre-heat system including a fuel pre-heat element having a fuel circuit fluidically connected to the at least one combustor arranged in a heat exchange relationship with a heating medium circuit fluidically connected to at least one of the compressor portion, the turbine portion, and the accessory.
    Type: Application
    Filed: November 9, 2012
    Publication date: May 15, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Bhaskar Pemmi, Joseph John, Indrajit Mazumder
  • Publication number: 20140102105
    Abstract: A system for heating combustor fuel includes a turbine exhaust plenum and a heat exchanger downstream from the turbine exhaust plenum. The heat exchanger has an exhaust inlet, an exhaust outlet, a fuel inlet, and a fuel outlet. An exhaust recirculation plenum has a recirculation inlet connection downstream from the exhaust outlet and a recirculation outlet connection upstream from the exhaust inlet. The system further includes structure for controlling a recirculated exhaust flow from the exhaust outlet into the exhaust recirculation plenum.
    Type: Application
    Filed: October 15, 2012
    Publication date: April 17, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Durgaprasad Janapaneedi, Korey Frederic Rendo, Dean Matthew Erickson, Timothy Russell Bilton, Christina Renee Pompey
  • Publication number: 20140102113
    Abstract: A system includes a gas turbine and an anti-icing system coupled to the gas turbine. The gas turbine is configured to receive air and fuel and to combust a mixture of the air and the fuel into exhaust gases. The anti-icing system is configured to use heat from the exhaust gases to heat a heat transfer fluid (HTF) and to selectively heat the fuel and the air via the HTF.
    Type: Application
    Filed: June 15, 2012
    Publication date: April 17, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Jose Antonio Cuevas, James Knox Prochaska
  • Publication number: 20140090387
    Abstract: A fuel heating system for a power plant includes an exhaust structure having an interior region for receiving an exhaust gas therein. Also included is a fluid injection arrangement comprising a first fluid duct for transferring a fluid, the first fluid duct extending at least partially throughout the interior region of the exhaust structure for heating the fluid. Further included is a heat exchanger for receiving the fluid and a liquid fuel, the fluid heating the liquid fuel during passage of the liquid fuel through the heat exchanger.
    Type: Application
    Filed: October 2, 2012
    Publication date: April 3, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Joseph John, Veerappan Muthaiah, Chandrasekhar Pushkaran, Prithviraj Pandian
  • Patent number: 8677755
    Abstract: A process for management of thermal effluents of an aircraft that includes an airframe (110) and at least one propulsion system (112), whereby the at least one propulsion system (112) includes a gas turbine engine (116) that is supplied with fuel via a fuel supply circuit (122) that extends from a reservoir (124) that is arranged at the airframe (110), whereby the airframe (110) includes at least one source of thermal effluents (134), wherein the process includes at least partially dissipating—at the level of at least one propulsion system (112)—the thermal effluents that are generated at the airframe (110) by using as coolant the fuel that is used for supplying the gas turbine engine (116).
    Type: Grant
    Filed: November 12, 2008
    Date of Patent: March 25, 2014
    Assignees: Airbus Deutschland GmbH, Airbus Operations S.A.S.
    Inventors: Guillaume Bulin, Jan Dittmar
  • Patent number: 8677729
    Abstract: An embodiment of the present invention takes the form of a system that uses exhaust from the combustion turbine engine to heat the fuel gas consumed by a combustion turbine engine. The benefits of the present invention include reducing the need to use a parasitic load to heat the fuel gas.
    Type: Grant
    Filed: October 25, 2011
    Date of Patent: March 25, 2014
    Assignee: General Electric Company
    Inventors: Timothy Russell Bilton, David Wesley Ball, Jr., Brian Michael Gallagher, Korey Frederic Rendo, Gary Cletus Mobley, Jr.
  • Publication number: 20140060057
    Abstract: A method of heating liquid fuel upstream of a combustor in a system where compressor discharge air is cooled before being supplied to fuel nozzles in the combustor includes the steps of passing the compressor discharge air through a heat exchanger in heat exchange relationship with the liquid fuel to heat the liquid fuel and cool the compressor discharge air; supplying the heated liquid fuel and the cooled compressor discharge air to the combustor.
    Type: Application
    Filed: September 5, 2012
    Publication date: March 6, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Joseph JOHN, Manikandan THIYAGARAJAN, Indrajit MAZUMDAR, Awanish KUMAR
  • Patent number: 8636247
    Abstract: A gas generator assembly includes a propellant chamber housing an amine based propellant. A reaction chamber is coupled with the propellant chamber. The reaction chamber includes a reaction chamber housing, and a porous reaction matrix within the reaction chamber housing. The reaction matrix includes a catalyzing agent, and the catalyzing agent is configured to non-combustibly catalyze the amine based propellant into one or more pressurized gases. An injector is in communication with the propellant chamber. The injector is configured to deliver the amine based propellant to the porous reaction matrix. A discharge nozzle is coupled with the reaction chamber and is configured to accelerate and discharge the one or more pressurized gases. In one example, the gas generator is coupled with one or more of an impulse turbine assembly and an electric generator to form a micro power unit.
    Type: Grant
    Filed: April 19, 2011
    Date of Patent: January 28, 2014
    Assignee: Raytheon Company
    Inventors: Jeremy C. Danforth, Richard D. Loehr, Kevin P. Murphy
  • Patent number: 8631655
    Abstract: The gas turbine engine comprises at least one electrical generator and an electrical heater associated with a gas path of the engine. The heater is powered by the generator to selectively add heat to the gas turbine cycle.
    Type: Grant
    Filed: February 19, 2010
    Date of Patent: January 21, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Kevin Allan Dooley
  • Patent number: 8584465
    Abstract: In a power plant which is equipped with a gas turbine, fuel for the gas turbine is preheated by means of solar heat. The preheating is realized through the use of a heat transfer circuit. The use of an additional, second heat transfer circuit between the source for the solar heat and the first heat transfer circuit permits storage of the solar heat. The fuel preheating according to the invention permits in particular an increase in the efficiency of the power plant.
    Type: Grant
    Filed: October 1, 2012
    Date of Patent: November 19, 2013
    Assignee: Alstom Technology Ltd.
    Inventors: Richard Carroni, Burkhard Josuhn-Kadner
  • Patent number: 8572975
    Abstract: A combustion turbine engine that includes: a compressor; a combustor that receives fuel from a fuel line; a turbine; a heat exchange portion comprising a portion of the fuel line in heat transfer relationship with a heat source for heating the fuel; a rapid heating value meter disposed to test the heating value of the fuel that is configured to provide heating value test results within approximately 1 minute; a cold leg bypass comprising a fuel line that bypasses the heat exchange portion, the cold leg bypass being connected to the fuel line at an upstream fork and at a fuel mixing junction; and valves for controlling the fuel being directed through the heat exchange portion and the fuel being direct through the cold leg bypass; wherein the length of fuel line between the fuel mixing junction and the combustor is less than 20 meters.
    Type: Grant
    Filed: June 8, 2009
    Date of Patent: November 5, 2013
    Assignee: General Electric Company
    Inventors: Timothy R. Bilton, Dean M. Erickson, Brian M. Gallagher, Korey F. Rendo, John V. Hains
  • Patent number: 8534073
    Abstract: An embodiment of the present invention may take the form of a system that may use the heat removed from an exhaust stream during an exhaust gas recirculation process to heat the fuel consumed by a turbomachine.
    Type: Grant
    Filed: October 27, 2008
    Date of Patent: September 17, 2013
    Assignee: General Electric Company
    Inventors: Andres J. Garcia-Crespo, Amit S. Toprani
  • Publication number: 20130232989
    Abstract: A fuel heating system for a gas turbine engine comprises a first heat exchanger, a second heat exchanger, a fuel pump and a valve. The first heat exchanger produces a heated air flow. The second heat exchanger receives the heated air flow from the first heat exchanger. The fuel pump provides a fuel flow. The valve is coupled to the fuel pump to intermittently include the second heat exchanger in the fuel flow based on a temperature of the fuel flow. A method of heating fuel in a gas turbine engine comprises providing fuel to a gas turbine engine with a fuel pump to sustain a combustion process, heating a flow of air with exhaust gas from the combustion process, and heating fuel from the fuel pump en route to the gas turbine engine with the flow of air based on a temperature of the fuel.
    Type: Application
    Filed: March 6, 2012
    Publication date: September 12, 2013
    Applicant: HAMILTON SUNDSTRAND CORPORATION
    Inventor: Omar I. Osorio
  • Patent number: 8528335
    Abstract: A system is provided and includes first and second water supplies at first and second relatively high and low temperatures, respectively, a heat exchanger, coupled to the water supplies, through which fuel and relative amounts of the water supplies at the first and second temperatures flow for fuel heating and a controller, operably interposed between the water supplies and the heat exchanger, to select and/or modulate the relative amounts of the water supplies permitted to flow through the heat exchanger to heat the fuel to a temperature based on a heating requirement to meet a modified wobbe index (MWI) rating.
    Type: Grant
    Filed: February 2, 2010
    Date of Patent: September 10, 2013
    Assignee: General Electric Company
    Inventors: Timothy Russell Bilton, Dean Matthew Erickson, Brian Michael Gallagher, Ravi Praveen Eluripati, Rakesh Sivasankaran