Plural Distinct Injectors Patents (Class 60/746)
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Patent number: 8209986Abstract: A protection system for a pre-mixing apparatus for a turbine engine, includes: a main body having an inlet portion, an outlet portion and an exterior wall that collectively establish a fuel delivery plenum; and a plurality of fuel mixing tubes that extend through at least a portion of the fuel delivery plenum, each of the plurality of fuel mixing tubes including at least one fuel feed opening fluidly connected to the fuel delivery plenum; at least one thermal fuse disposed on an exterior surface of at least one tube, the at least one thermal fuse including a material that will melt upon ignition of fuel within the at least one tube and cause a diversion of fuel from the fuel feed opening to at least one bypass opening. A method and a turbine engine in accordance with the protection system are also provided.Type: GrantFiled: October 29, 2008Date of Patent: July 3, 2012Assignee: General Electric CompanyInventors: Benjamin Paul Lacy, Lewis Berkley Davis, Jr., Thomas Edward Johnson, William David York
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Publication number: 20120151931Abstract: An engine includes: (1) a housing defining a combustion chamber; (2) a set of injection mechanisms connected to the housing and configured to introduce a fuel and nanoparticles into the combustion chamber; and (3) an optical ignition system connected to the housing and configured to irradiate the nanoparticles to ignite the fuel.Type: ApplicationFiled: December 14, 2011Publication date: June 21, 2012Applicant: The Board of Trustees of the Leland Stanford Junior UniversityInventors: Xiaolin Zheng, Yuma Ohkura
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Publication number: 20120151930Abstract: A pilot fuel injector tip includes concentric primary and secondary pilot fuel nozzles having a circular primary exit axially aft and downstream of an annular secondary exit respectively. A fuel nozzle assembly includes a pilot swirler flowpath section having an annular inwardly tapering conical flowpath section surrounding primary and secondary exits. An inwardly tapering conical wall section radially inwardly bounding flowpath section defines a conical surface. Exits are located at or axially forward or upstream of the conical surface. An annular secondary fuel supply passage in secondary pilot fuel nozzle includes a secondary fuel swirler with an array of helical spin slots that may have rectangular cross sections. A chamfered leading edge of an annular wall section disposed between an outer pilot swirler and an inlet to an injector cooling flowpath surrounding the second pilot swirler includes a radially inwardly facing conical chamfered surface for deflecting dirt from cooling flowpath.Type: ApplicationFiled: December 17, 2010Publication date: June 21, 2012Inventors: Nayan Vinodbhai Patel, Michael Anthony Benjamin, Duane Douglas Thomsen, Alfred Albert Mancini
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Publication number: 20120151927Abstract: A unitary fuel injection manifold for a secondary fuel nozzle improves fuel-air mixing and offers flexibility to alter the mixing profile through adaptability to a variety of number, types, and orientation of discharge outlets to the combustion air mixing space around the secondary fuel nozzle. An aerodynamic surface with reduced extension into the mixing space reduces pressures drop and interference with design airflow. Manifold integrity is enhanced by elimination of fillet welds to mount external pegs.Type: ApplicationFiled: December 17, 2010Publication date: June 21, 2012Inventors: Divyang Rajendra Desai, Sandeep Gopalakrishna, Kodukulla Venkat Sridhar, Amit Monga
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Patent number: 8192688Abstract: A thermally diluted exothermic reactor system is comprised of numerous orifices distributed within a combustor by distributed perforated contactor tubes or ducts. The perforated contactors deliver and mix diluent fluid and one or more reactant fluids with an oxidant fluid. Numerous micro-jets about the perforated tubes deliver, mix and control the composition of reactant fluid, oxidant fluid and diluent fluid. The reactor controls one or more of composition profiles, composition ratio profiles and temperature profiles in one or more of the axial direction and one or two transverse directions, reduces temperature gradients and improves power, efficiency and emissions.Type: GrantFiled: March 26, 2009Date of Patent: June 5, 2012Assignee: Vast Power Portfolio LLCInventors: David L. Hagen, Gary Ginter, Bill Goheen, L. Allan McGuire, Janet Rankin
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Publication number: 20120125008Abstract: A combustion system for a gas turbine engine includes a housing defining a pressure vessel. A master injector is mounted to the housing for injecting fuel along a central axis defined through the pressure vessel. A plurality of slave injectors is included. Each slave injector is disposed radially outward of and substantially parallel to the master injector for injecting fuel and air in an injection plume radially outward of fuel injected through the master injector. The master injector and slave injectors are configured and adapted so the injection plume of the master injector intersects with the injection plumes of the slave injectors. The slave injectors can be staged for reduced power operation.Type: ApplicationFiled: November 24, 2010Publication date: May 24, 2012Applicant: Delavan IncInventors: Lev Alexander Prociw, Andy W. Tibbs
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Patent number: 8176739Abstract: The low emission combustor includes a combustor housing defining a combustion chamber having a plurality of combustion zones. A liner sleeve is disposed in the combustion housing with a gap formed between the liner sleeve and the combustor housing. A secondary nozzle is disposed along a centerline of the combustion chamber and configured to inject a first fluid comprising air, at least one diluent, fuel, or combinations thereof to a downstream side of a first combustion zone among the plurality of combustion zones. A plurality of primary fuel nozzles is disposed proximate to an upstream side of the combustion chamber and located around the secondary nozzle and configured to inject a second fluid comprising air and fuel to an upstream side of the first combustion zone. The combustor also includes a plurality of tertiary coanda nozzles. Each tertiary coanda nozzle is coupled to a respective dilution hole.Type: GrantFiled: July 17, 2008Date of Patent: May 15, 2012Assignee: General Electric CompanyInventors: Andrei Tristan Evulet, Balachandar Varatharajan, Gilbert Otto Kraemer, Ahmed Mostafa ElKady, Benjamin Paul Lacy
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Patent number: 8177547Abstract: The invention relates to a method for starting a burner for combusting synthesis gases, wherein said burner comprises first and second fuel passages, the first fuel passage encompasses the second fuel passage in a substantially concentric manner and the gas transferred to the burner is mixed with combusting air and is combusted. According to said invention, in order to start the burner, the second fuel passage is first loaded with a synthesis gas to a predefined burner power at a first starting phase and the first fuel passage is loaded with the synthesis gas at a second starting phase.Type: GrantFiled: November 15, 2005Date of Patent: May 15, 2012Assignee: Siemens AktiengesellschaftInventors: Berthold Köstlin, Frank Hannemann, Andreas Heilos, Gerhard Zimmermann
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Publication number: 20120110974Abstract: A gas turbine engine is provided and includes a combustor having a first interior in which a first fuel is combustible, a turbine into which products of at least the combustion of the first fuel are receivable, a transition zone, including a second interior in which a second fuel and the products of the combustion of the first fuel are combustible, a plurality of fuel injectors which are configured to supply the second fuel to the second interior in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages, a compressor, by which air is supplied to the first and second interiors for the combustion therein, and a control system configured to control relative amounts of the air to the first and second interiors and relative amounts of the first and second fuels supplied to the first and second interiors.Type: ApplicationFiled: January 6, 2012Publication date: May 10, 2012Applicant: GENERAL ELECTRIC COMPANYInventors: Lewis Berkley Davis, JR., Krishna Kumar Venkataraman, Willy Steve Ziminsky, Geoffrey David Myers
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Patent number: 8172568Abstract: A combustor, in which a flame holding region is formed at a location distant from a pilot burner to avoid burnout of the pilot burner and in which flame holding capability is increased to use a lean pre-mix gas for reducing NOx emission, is provided. The combustor includes a combustion liner having a cylindrical side wall that defines a combustion chamber; and a main burner positioned at a top portion of the combustion liner for injecting an annular pre-mix gas into the combustion chamber to form a reverse flow region at a downstream portion thereof, which region is oriented towards the top portion of the combustion chamber along a longitudinal axis. In this combustor, a pilot burner is arranged at the top portion for injecting a mixture of fuel and air only in a direction confronting the reverse flow region.Type: GrantFiled: February 4, 2010Date of Patent: May 8, 2012Assignee: Kawasaki Jukogyo Kabushiki KaishaInventors: Hiroyuki Kashihara, Yasushi Yoshino, Kiyoshi Matsumoto, Takeshi Kimura, Junichi Kitajima, Atsushi Horikawa
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Publication number: 20120090291Abstract: An internal combustion engine in which the power output is controlled by modulating at least one of the compression ratio, expansion ratio, ratio of expansion rate to compression rate, air to fuel ratio, and steam to air ratio. Continuous isobaric catalytic combustion followed by isothermal expansion and the use of separate compressor and expander devices are used. Control dynamically maximizes fuel efficiency for the given power demand conditions. Power output is controlled by modulating flame temperature and/or pressure instead of by throttling. Lean combustion, high compression ratio, exhaust heat recuperation, and high power density and fuel economy are provided. External cooling is minimized or eliminated. Insulation of the engine effectively reduces energy losses to friction. Interchangeable use of gasoline, hydrogen and ammonia at high fuel efficiency is made possible for transitional periods of fuel availabilities. An injector suitable for isothermal expansion is provided.Type: ApplicationFiled: November 23, 2011Publication date: April 19, 2012Inventor: Jonathan Jay FEINSTEIN
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Patent number: 8156744Abstract: An annular gas turbine engine combustion chamber including an outer wall and an inner wall connected by a wall forming the chamber bottom is disclosed. The walls delimit sources of combustion with axes inclined relative to the axis of the chamber. The chamber-bottom wall, of frustoconical shape, is pierced with orifices for the fuel injection systems, the planes of the orifices being perpendicular to the axes of the sources of combustion. The combustion chamber also includes heat-protection baffles centered on each of the orifices with a shoulder by which they rest against a flat surface portion along the periphery of the orifices. The chamber-bottom wall is conformed in a succession of adjacent flat facets having a common edge, with one facet per orifice, and the shoulder of the deflectors pressing against the plane of the facets.Type: GrantFiled: September 19, 2008Date of Patent: April 17, 2012Assignee: SNECMAInventors: Didier Hippolyte Hernandez, Thomas Olivier Marie Noel
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Publication number: 20120085099Abstract: A system and method for tuning a gas turbine combustion system having a plurality of seals positioned between the combustion system and the turbine inlet is disclosed. The system and method provide ways of permitting a predetermined amount of compressed air to bypass the combustion system and enter the turbine so as to control emissions and dynamics of the combustion system. The seals contain a plurality of holes to meter airflow passing therethrough and are positioned such that they can be removed from the engine and modified to increase or decrease the amount of air passing therethrough.Type: ApplicationFiled: October 8, 2010Publication date: April 12, 2012Applicant: ALSTOM TECHNOLOGY LTDInventors: Sherman Craig Creighton, Charles Ellis, David John Henriquez, Peter Stuttaford
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Publication number: 20120073300Abstract: A combustor includes an end cover and a combustion chamber downstream of the end cover. The combustor further includes nozzles disposed radially in the end cover and a shroud surrounding at least one of the nozzles and extending downstream into the combustion chamber. The shroud includes an inner wall surface and an outer wall surface. A method for operating a combustor includes flowing compressed working fluid through nozzles into a combustion chamber, flowing fuel through each nozzle in a first subset of the nozzles into the combustion chamber, and igniting the fuel from each nozzle in the first subset of nozzles in the combustion chamber. In addition, the method includes extending into the combustion chamber a separate shroud around each nozzle in a second subset of the nozzles and isolating fuel to each nozzle in the second subset of nozzles.Type: ApplicationFiled: September 24, 2010Publication date: March 29, 2012Applicant: GENERAL ELECTRIC COMPANYInventors: Willy Steve Ziminsky, Christopher Edward Wolfe, Sergey Anatolievich Meshkov, Sergey Adolfovich Oskin
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Publication number: 20120073301Abstract: A fuel delivery system for delivering fuel to a gas turbine engine includes a fixed critical flow nozzle, a first fuel nozzle and a second fuel nozzle. The fixed critical flow nozzle and the variable critical flow nozzle are connected to a fuel source in parallel. The fixed critical flow nozzle has an orifice throat with a fixed effective cross-sectional area. The variable critical flow nozzle has an orifice throat with a variable effective cross-sectional area. The first fuel nozzle is connected to the fixed critical flow nozzle for delivering fuel to the gas turbine engine, and the second fuel nozzle is connected to the variable critical flow nozzle for delivering fuel to the gas turbine engine.Type: ApplicationFiled: September 27, 2010Publication date: March 29, 2012Applicant: HAMILTON SUNDSTRAND CORPORATIONInventor: Bruce Paradise
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Patent number: 8145403Abstract: A method and algorithm are provided to operate a gas turbine at baseload in an emission compliant capable mode to avoid combustion dynamics while operating with cold fuel and hot fuel combustion hardware. The method includes performing a gas turbine operational sequence such as a startup to an emission compliant capable mode. A gas fuel temperature is measured. The gas turbine is operated in the emissions compliant capable mode according to a designated fuel split for avoiding combustion dynamics when a temperature for a gas fuel is below a designated value. A determination is made whether a modified wobbe index for the gas fuel is below an emissions compliant value. An alarm is activated if the modified wobbe index is below the emissions compliant value to notify the operator of a potential emissions shift.Type: GrantFiled: December 31, 2008Date of Patent: March 27, 2012Assignee: General Electric CompanyInventors: Jason D. Fuller, Garth C. Frederick, John C. Maters, Douglas C. Morgan, Luls M. Flamand
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Patent number: 8132415Abstract: Disclosed herein are a fuel nozzle of a gas turbine combustor for dimethyl ether (DME, CH3OCH3) and a design method thereof. The fuel nozzle includes a pilot fuel injection hole formed at the center of the nozzle and a plurality of fuel injection ports formed at equiangular positions around the pilot fuel injection hole to inject DME. Each of the fuel injection ports includes a pair of upper and lower DME injection orifices communicating with a fuel-air mixture injection swirler. The upper DME injection orifice becomes gradually wider, whereas the lower DME injection orifice becomes gradually narrower. Thus, DME can be optimally combusted in the gas turbine combustor, thereby achieving cost reduction of power plants, enhancement in reliability of the power plants, and diversification of usable fuel.Type: GrantFiled: June 25, 2008Date of Patent: March 13, 2012Assignee: Korea Electric Power CorporationInventors: Min Chul Lee, Dal Hong Ahn, Yong Jin Joo, Seok Bin Seo, Jae Hwa Chung, Won Shik Park, Hae Kyung Seo
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Publication number: 20120055164Abstract: Annular combustion chamber (10) to be fitted on a turbomachine and comprising a chamber end wall (22), a plurality of air and fuel injection systems (32) circumferentially distributed around an axis (34) of the combustion chamber (10) and mounted on said chamber end wall (22), and, an air manifold (100) associated with each injection system (32), comprising at least one wall (96, 98) mounted on the chamber end wall (22) and projecting in the upstream direction to form an obstacle to a circumferential airflow around the axis (34) of the combustion chamber (10), and an air inlet opening (88) formed at the upstream end of the air manifold (100) and opening radially outwards from an axis (44) of said injection system.Type: ApplicationFiled: March 15, 2010Publication date: March 8, 2012Applicant: SNECMAInventors: Sebastien Alain, Christophe Bourgois, Romain Nicolas Lunel, Thomas Olivier, Marie Noel
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Publication number: 20120055162Abstract: The lance of a burner includes a body that defines a first duct with first nozzles for injecting a liquid fuel and a second duct with second nozzles for injecting a gaseous fuel. Outlets of the first nozzles are spaced apart from outlets of the second nozzles. The body includes a third duct with third and fourth nozzles for injecting air. The third nozzles surround an axis of the first nozzles and the fourth nozzles surround an axis of the second nozzles.Type: ApplicationFiled: June 22, 2011Publication date: March 8, 2012Applicant: ALSTOM Technology LtdInventors: Adnan EROGLU, Johannes Buss, Andrea Ciani
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Patent number: 8127549Abstract: A burner is provided that has high flame stability and reduces NOx emissions. In the burner, air holes of an air hole member have a central axis inclined relative to a burner central axis. The leading end portion of a first fuel nozzle is configured to be able to suppress turbulence of air-flow flowing on the outer circumference side of the first fuel nozzle. The tip of the first fuel nozzle is located on a fuel jetting-out directional downstream side of the inlet of the fuel hole. The tip of the second fuel nozzle is located on a fuel jetting-out directional downstream side of the air hole inlet.Type: GrantFiled: November 26, 2008Date of Patent: March 6, 2012Assignee: Hitachi, Ltd.Inventors: Keisuke Miura, Hiroshi Inoue, Kazuhito Koyama, Takeo Saito, Satoshi Dodo
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Publication number: 20120047903Abstract: An injector includes a main nozzle body defining a central axis and having a main fuel circuit. A pilot nozzle body is mounted inboard of the main nozzle body. The pilot nozzle body includes a pilot air circuit on the central axis with fuel circuitry radially outboard of the pilot air circuit for delivering fuel to a fuel outlet in a downstream portion of the pilot nozzle body. The fuel circuitry includes a primary pilot fuel circuit configured and adapted to deliver fuel to the fuel outlet and a secondary pilot fuel circuit configured and adapted to deliver fuel to the same fuel outlet.Type: ApplicationFiled: November 9, 2011Publication date: March 1, 2012Applicant: Delavan Inc.Inventors: Brandon P. Williams, Viraphand Cholvibul, David H. Bretz
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Publication number: 20120047896Abstract: A combustion device includes a plurality of mixing devices into which a fluid containing oxygen and a fuel are introduced and mixed to form a mixture. The combustion device also includes a combustion chamber in which the mixture formed in the mixing devices is burnt. Each mixing device has a conical body with a lance projecting into the conical body, where the fuel is injectable into the conical body. Tips of the lances of different mixing devices have different distances from corresponding open ends of the respective conical bodies.Type: ApplicationFiled: August 25, 2011Publication date: March 1, 2012Applicant: ALSTOM Technology LtdInventors: Marta DE LA CRUZ GARCIA, Nicolas Noiray, Ghislain Singla
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Publication number: 20120036824Abstract: A reheat burner (1) includes a channel (2) with a lance (3) protruding thereinto to inject a fuel over an injection plane (4) perpendicular to a channel longitudinal axis (15). The channel (2) and lance (3) define a vortex generation zone (6) upstream of the injection plane (4) and a mixing zone (9) downstream of the injection plane (4) in the hot gas (G) direction. The mixing zone (9) includes a high speed area (16) with a constant cross section, and a diffusion area (17) with a flared cross section downstream of the high speed area (16) in the hot gas (G) direction.Type: ApplicationFiled: August 2, 2011Publication date: February 16, 2012Inventors: Johannes Buss, Andrea Ciani, Adnan Eroglu, Urs Benz, Michael DÜSING, Michael Hutapea
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Publication number: 20120031099Abstract: A combustor assembly that includes a combustor liner having a centerline axis and defining a combustion chamber there within. A plurality of fuel nozzles extends through the combustion liner. An annular flowsleeve is coupled radially outward from the combustor liner such that an annular flow path is defined between the flowsleeve and the combustor liner. The flowsleeve includes a forward surface that extends between an upper endwall and a lower endwall. The upper endwall is positioned a first distance from the plurality of fuel nozzles. The lower endwall is positioned a second distance from the plurality of fuel nozzles that is different than the first distance.Type: ApplicationFiled: August 4, 2010Publication date: February 9, 2012Inventors: Mahesh Bathina, Ramanand Singh
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Publication number: 20120031102Abstract: A combustor cap assembly for a turbine engine includes a combustor cap and a plurality of fuel nozzles mounted on the combustor cap. One or more of the fuel nozzles would include two separate fuel circuits which are individually controllable. The combustor cap assembly would be controlled so that individual fuel circuits of the fuel nozzles are operated or deliberately shut off to provide for physical separation between the flow of fuel delivered by adjacent fuel nozzles and/or so that adjacent fuel nozzles operate at different pressure differentials. Operating a combustor cap assembly in this fashion helps to reduce or eliminate the generation of undesirable and potentially harmful noise.Type: ApplicationFiled: August 5, 2010Publication date: February 9, 2012Inventors: Jong Ho UHM, Thomas Edward Johnson, Kwanwoo Kim
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Publication number: 20120023952Abstract: A nozzle for assemblies and gas turbines is provided. The nozzle exhibits destabilized flame holding characteristics, i.e., the nozzle is unable to stabilize flame up to an equivalence ratio of about 0.65. As a result, flame heat release is delayed resulting in lower peak flame temperatures and correspondingly lower NOx levels. Flame stabilization capability is retained for higher equivalence ratios to support operation of the combustor in other regions of the load range.Type: ApplicationFiled: July 30, 2010Publication date: February 2, 2012Applicant: GENERAL ELECTRIC COMPANYInventors: Christian Lee Vandervort, Joel Meier Haynes
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Patent number: 8104284Abstract: A combustor includes a chamber mixing and burning fuel and air and an air hole plate disposed on a wall surface of the chamber. The, air hole plate includes a plurality of rows disposed concentrically of a plurality of air holes jetting coaxial jets of fuel and air into the chamber. A first fuel nozzle and a second fuel nozzle are disposed near a fuel hole for jetting fuel into an air hole row on an inner peripheral side. The first fuel nozzle is structured to suppress turbulence of a surrounding air flow and the second fuel nozzle is structured to promote turbulence of a surrounding air flow. In accordance with the aspect of the present invention, good flame stability can be maintained while further reducing NOx in a combustor using coaxial jets.Type: GrantFiled: April 23, 2008Date of Patent: January 31, 2012Assignee: Hitachi, Ltd.Inventors: Keisuke Miura, Hiroshi Inoue, Kazuhito Koyama, Takeo Saito
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Patent number: 8091362Abstract: A fuel nozzle is provided. The fuel nozzle includes a heat shield, a fuel tube and a plurality of support members. The support members are radially interposed between the heat shield and the fuel tube. The support members are preferably cylindrical tubes, thus creating voids or pockets between the heat shield and the fuel tube. The cylindrical tubes are connected to one another at a first end are free at an opposed end. As such, the tubes can move or slide relative to one another. Further, the tubes preferably only contact one another with at most line contacts. The fuel nozzle may also include a tip portion that includes a tip heat shield that extends radially outward from the primary heat shield. The tip heat shield defines a cavity that connects with the central cavity of the heat shield. The fuel tube extends through the tip heat shield.Type: GrantFiled: August 20, 2008Date of Patent: January 10, 2012Assignee: Woodward, Inc.Inventor: David S. Smith
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Patent number: 8047002Abstract: The present invention relates to an annular combustion chamber of a gas turbine engine comprising a casing with at least one air tapping outlet situated at the chamber inlet, a fuel supply device with a plurality of fuel injectors in the chamber distributed annularly of which at least one is situated close to said tapping outlet. The chamber is characterized in that the fuel supply device comprises a means for reducing the fuel flow rate in said injector situated close to the tapping outlet relative to the other fuel injectors. Thanks to the invention, the hot spots downstream of the combustion chamber caused by the tappings are reduced.Type: GrantFiled: October 28, 2008Date of Patent: November 1, 2011Assignee: SNECMAInventors: Christophe Pieussergues, Denis Jean Maurice Sandelis
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Patent number: 8037689Abstract: A fuel nozzle for a turbine is disclosed. The fuel nozzle includes a housing, a plurality of fuel passages disposed within the housing, and a plurality of air passages disposed within the housing. A total flow area of the plurality of fuel passages is substantially equal to a total flow area of the plurality of air passages.Type: GrantFiled: August 21, 2007Date of Patent: October 18, 2011Assignee: General Electric CompanyInventors: Sergey Adolfovich Oskin, Mark Allan Hadley, Joel Meador Hall, Sergey Konstantinovich Yerokhin, Sergey Anatolievich Meshkov
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Publication number: 20110247314Abstract: A gas turbine combustor includes a combustion chamber defined by a combustor liner, the combustor liner having an upstream end cover supporting one or more nozzles arranged to supply fuel to the combustion chamber where the fuel mixes with air supplied from a compressor. A transition duct is connected between an aft end of the combustion chamber liner and a first stage turbine casing, the transition duct supplying gaseous products of combustion to the first stage turbine nozzle. One or more additional fuel injection nozzles are arranged at an aft end of the transition duct for introducing additional fuel into the transition duct upstream of the first stage turbine nozzle.Type: ApplicationFiled: April 12, 2010Publication date: October 13, 2011Applicant: GENERAL ELECTRIC COMPANYInventors: Ronald James CHILA, Mark HADLEY
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Patent number: 8033117Abstract: A method for controlling NOx emissions from a gas turbine having a fuel adjustment system may include setting an outer nozzle fuel flow to achieve a desired level of combustion dynamics for at least one of a plurality of combustion chambers, determining a delta adjustment value for a center nozzle fuel flow that will result in a desired level of NOx emissions from the gas turbine, and adjusting the center nozzle fuel flow according to the determined delta adjustment value to obtain the desired level of NOx emissions from the gas turbine.Type: GrantFiled: September 18, 2008Date of Patent: October 11, 2011Assignee: General Electric CompanyInventors: Willy Steve Ziminsky, Scott Kopcho, Mark P. Bombard, Anthony Joseph Antonucci
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Publication number: 20110239658Abstract: Systems and methods for injection of feedstock are included. In one embodiment, a system includes a solid fuel injector. The solid fuel injector includes a solid fuel passage, a first gas passage, and a second gas passage. The solid fuel passage is configured to inject a solid fuel through a fuel outlet in a fuel direction. The first gas passage is configured to inject a first gas through a first gas outlet in a first gas direction. The second gas passage is configured to inject a second gas through a second gas outlet in a second gas direction. The first gas direction is oriented at a first angle relative to the fuel direction. The second gas direction is oriented at a second angle relative to the fuel direction, and the first and second angles are different from one another.Type: ApplicationFiled: April 6, 2010Publication date: October 6, 2011Applicant: General Electric CompanyInventor: Benjamin Campbell Steinhaus
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Patent number: 8028512Abstract: A combustion control system for a turbine engine is disclosed. The combustion control system includes a fuel injector having a main fuel supply and pilot fuel supply coupled to a combustor of the turbine engine. The combustion control system also includes a sensor coupled to a transfer tube. The transfer tube is fluidly coupled to the combustor, and the sensor is configured to detect a pressure pulse in the combustor. A semi-infinite coil is also coupled to the transfer tube. The combustion control system also includes a controller electrically connected to the sensor. The controller is configured to compare an amplitude of the pressure pulse within a frequency range to a threshold amplitude, and adjust the pilot fuel supply in response to the comparison.Type: GrantFiled: November 28, 2007Date of Patent: October 4, 2011Assignee: Solar Turbines Inc.Inventors: Robert Eleazar Mendoza, Paul Elliot Morrison, Marco Ezra Leon, Tiziano Marco Bognuda, Satoshi Ito, Shari Turner, legal representative
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Publication number: 20110232296Abstract: According to one aspect of the invention, a combustor is disclosed. The combustor can include a combustor housing, a plurality of nozzles disposed within the combustor housing, and a flame detector disposed on and in optical communication with each of the plurality of fuel nozzles, wherein each flame detector is configured to detect an optical property related to at least one of a flame holding condition and a flashback condition in a respective fuel nozzle.Type: ApplicationFiled: March 24, 2010Publication date: September 29, 2011Applicant: GENERAL ELECTRIC COMPANYInventor: Garth Curtis Frederick
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Publication number: 20110225974Abstract: A method of operating a combustor includes delivering a primary fuel flow through a plurality of primary fuel nozzles toward a primary combustion zone and combusting the primary fuel flow in the primary combustion zone. A secondary fuel flow is delivered through a secondary fuel nozzle toward a secondary combustion zone and combusted therein. The secondary fuel is located such that the plurality of primary fuel nozzles are arrayed around the secondary fuel nozzle. An outer swirler is located between the plurality of primary fuel nozzles and the secondary fuel nozzle and includes a plurality of outer swirler channels extending therethrough. A flow of swirler fuel is delivered through the plurality of outer swirler channels into the combustor substantially between the primary combustion zone and the secondary combustion zone to stabilize combustion in the primary combustion zone and/or the secondary combustion zone.Type: ApplicationFiled: March 22, 2010Publication date: September 22, 2011Applicant: GENERAL ELECTRIC COMPANYInventors: Abdul Rafey Khan, Thomas Edward Johnson
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Publication number: 20110209481Abstract: An end cover assembly for a combustor includes a first plate receptive of one of more combustor fuel nozzles and a second plate. One or more intermediate plates are located between the first plate and the second plate and define one or more cavities to distribute fuel to one or more combustor fuel nozzles. The first plate, the second plate, and the one or more intermediate plates are secured in a stack.Type: ApplicationFiled: February 26, 2010Publication date: September 1, 2011Applicant: GENERAL ELECTRIC COMPANYInventor: Scott Robert Simmons
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Publication number: 20110203285Abstract: A burner arrangement is provided. The burner arrangement includes a support and at least two fuel nozzles attached to the support in the direction of flow, with each fuel nozzle including a support-side section which includes a contact surface on the support side with which it rests on a supporting surface of the support, with at least two fuel nozzle tips embodied in one piece extending out from the support-side section in the direction of flow and the support-side contact surface including at least two extension parts projecting in the direction of the support, with the extension parts each embodying a channel through which fuel is fed in each case to the fuel nozzle tips through passages which are arranged in the support-side contact surface of the support-side section.Type: ApplicationFiled: February 17, 2011Publication date: August 25, 2011Inventors: Andreas Böttcher, Timothy A. Fox, Thomas Grieb, Tobias Krieger, Stephen A. Ramier
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Publication number: 20110197588Abstract: A fuel injector nozzle is disclosed. The nozzle includes a nozzle body for fluid communication of a liquid fuel to produce a liquid fuel jet and a fluid to produce a fluid jet. The nozzle body includes an adapter comprising a fuel conduit and a fluid conduit. The nozzle body also includes a nozzle tip disposed on the adapter comprising a plurality of fuel outlet conduits that are in fluid communication with the fuel conduits and a plurality of fluid outlet conduits that are in fluid communication with the fluid conduits.Type: ApplicationFiled: February 12, 2010Publication date: August 18, 2011Applicant: GENERAL ELECTRIC COMPANYInventors: Sachin Khosla, Mihir Lal, Daniel Scott Zehentbauer
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Publication number: 20110197591Abstract: A combustor for a gas turbine includes a plurality of radially outer nozzles arranged in an annular array, each of the radially outer nozzles having an outlet end located to supply fuel and/or air to a first combustion chamber. A center nozzle has an outlet end located axially upstream of the outlet ends of the radially outer nozzles, and is configured and arranged to supply fuel and air to a second combustion chamber axially upstream of the first combustion chamber. The second combustion chamber opens into the first combustion chamber and has a length sufficient to maintain a center nozzle flame confined to the second combustion chamber.Type: ApplicationFiled: February 11, 2011Publication date: August 18, 2011Inventors: Almaz Valeev, Sergey Anatolievich Meshkov, Mark Hadley, Stanley Widener, Geoffrey Myers, Valery Alexandrovich Mitrofanov
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Publication number: 20110197594Abstract: A method of controlling a combustor of a gas turbine is disclosed. The method includes operatively disposing a combustor can in a combustor of a gas turbine. The combustor can comprising a plurality of combustor fuel nozzles, each having a fuel injector and configured to selectively provide a liquid fuel, a liquid fluid or liquid fuel and liquid fluid to a fuel injector nozzle that is configured to provide, respectively, a plurality of liquid fuel jets, a plurality of liquid fluid jets or a combination thereof, that are in turn configured to provide an atomized liquid fuel stream, an atomized liquid fluid stream, or an atomized and emulsified liquid fuel-liquid fluid stream, respectively. The method also includes selectively providing an amount of fuel, fluid or a combination thereof to the fuel injector nozzle to produce an atomized fuel stream, atomized fluid stream, or an atomized and emulsified fuel-fluid stream, respectively.Type: ApplicationFiled: February 12, 2010Publication date: August 18, 2011Applicant: GENERAL ELECTRIC COMPANYInventors: Sachin Khosla, Mihir Lal, Daniel Scott Zehentbauer
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Publication number: 20110197589Abstract: A fuel injector nozzle is disclosed. The nozzle includes a nozzle body having a fuel conduit that extends from a fuel inlet through a fuel outlet conduit to a fuel outlet and a fluid conduit that extends from a fluid inlet through a fluid outlet conduit to a fluid outlet. The fuel outlet conduit and fuel outlet configured to produce a liquid fuel jet from the fuel outlet upon introduction of a pressurized liquid fuel into the fuel conduit. The fluid outlet conduit and fluid outlet are configured to produce a liquid fluid jet from the fluid outlet upon introduction of a pressurized liquid fluid into the fluid conduit, wherein the liquid fuel jet and the liquid fluid jet are configured to impact one another and produce a flow stream of atomized fuel.Type: ApplicationFiled: February 12, 2010Publication date: August 18, 2011Applicant: GENERAL ELECTRIC COMPANYInventors: Sachin Khosla, Mihir Lal, Daniel Scott Zehentbauer
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Publication number: 20110185735Abstract: An annular combustor for a gas turbine engine is provided that facilitates staged combustion in a lean direct ignition (LDI) mode over an extended range of operating fuel air ratios. A method is also provided for operating a gas turbine engine over a power demand range that facilitates staged combustion in a lean direct ignition (LDI) mode over an extended range of operating fuel air ratios.Type: ApplicationFiled: January 29, 2010Publication date: August 4, 2011Applicant: United Technologies CorporationInventor: Timothy S. Snyder
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Publication number: 20110179797Abstract: A burner and a method for operating a burner are provided. The burner includes a channel having a mixing zone and having a feed for an oxidation means, particularly an air feed, and at least one fuel feed for injecting fuel, wherein a separating means which divides the channel over a wide range of the channel into at least two separated channels, namely a first channel and a second channel, is provided in the channel. The method for operating a burner having a channel includes a mixing zone into which an oxidation mass flow and fuel are injected, wherein two substantially separate flow paths are formed by means of a separating means in the channel and the at least two separated first and second channels, formed by the separating means.Type: ApplicationFiled: September 14, 2009Publication date: July 28, 2011Inventor: Bernd Prade
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Publication number: 20110167832Abstract: A method for operating a premix burner for gaseous fuels having a multi-stage pilot gas system whose diffusion fuel is injected into a flame chamber of the premix burner as at least two partial streams with different orientations, and a premix burner for carrying out the method.Type: ApplicationFiled: November 3, 2008Publication date: July 14, 2011Applicant: MAN Diesel & Turbo SEInventors: Eric Norster, Holger Huitenga, Reiner Brinkmann
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Publication number: 20110162376Abstract: A system is provided that comprises a gasifier with an enclosure disposed about a chamber, wherein the enclosure comprises a top wall, a bottom wall, and a side wall between the top and bottom walls. The gasifier also comprises an outlet disposed in the bottom wall, a first injector disposed in the top wall, and a second injector disposed in the side wall, wherein the first and second injectors are configured to inject fuel, oxygen, or a combination thereof, into the chamber.Type: ApplicationFiled: January 7, 2010Publication date: July 7, 2011Applicant: General Electric CompanyInventor: Cliff Yi Guo
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Publication number: 20110162379Abstract: A nozzle includes first, second, and third ports each angled to direct a first, second, and third fluid in a first, second, and third rotational direction, respectively. The first, second, and third fluids are selected from the group consisting of a first fuel, a second fuel, a diluent, and a compressed working fluid. A method for supplying fuel through a nozzle includes injecting a first fluid through first ports in a first rotational direction, injecting a second fluid through second ports in a second rotational direction, and injecting a third fluid through third ports in a third rotational direction. The method further includes selecting the first, second, and third fluids from the group consisting of a first fuel, a second fuel, a diluent, and a compressed working fluid.Type: ApplicationFiled: January 6, 2010Publication date: July 7, 2011Applicant: GENERAL ELECTRIC COMPANYInventors: ABINASH BARUAH, ANAND PRAFULCHANDRA DESAI
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Publication number: 20110162375Abstract: Systems are provided for supplying fuel to secondary combustion zones within gas turbine engines. In one embodiment, a system includes a transition piece support structure extending from a compressor casing and configured to support a combustor transition piece of a gas turbine engine. A fuel passageway is integrated with the support structure.Type: ApplicationFiled: January 5, 2010Publication date: July 7, 2011Applicant: General Electric CompanyInventor: Jonathan Dwight Berry
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Patent number: 7941923Abstract: A secondary fuel nozzle is formed by brazing and welding a central core, a cylindrical body, and a unitary secondary fuel nozzle portion. The central core has a central bore for receiving a liquid fuel cartridge, and at least two passages concentric with the central bore. The secondary fuel nozzle portion includes a base flange and a main shaft having a central bore for aligning with the central bore of the core and for receiving the liquid fuel cartridge, and a plurality of peripheral bores disposed at spaced locations about the central bore for flow communication with the concentric passages of the core. The core is brazed to the base flange and the cylindrical body is disposed around the core and welded to the base flange to define a one-piece secondary fuel nozzle assembly.Type: GrantFiled: February 17, 2010Date of Patent: May 17, 2011Assignee: General Electric CompanyInventor: William Kirk Hessler
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Publication number: 20110107765Abstract: In certain embodiments, a system includes a gas turbine controller. The gas turbine controller includes a first operational mode enabling fuel flow only through a first plurality of fuel nozzles having a first swirl direction. The gas turbine controller also includes a second operational mode enabling fuel flow only through a second plurality of fuel nozzles having a second swirl direction opposite from the first swirl direction.Type: ApplicationFiled: July 7, 2010Publication date: May 12, 2011Applicant: GENERAL ELECTRIC COMPANYInventors: Almaz Valeev, Sergey Meshkov, Garth Frederick, Valery Mitrofanov, Dmitry Lysenko