Injectors In Distinct Radially Spaced Parallel Flow Combustion Products Generators Arranged To Combine Discharges Patents (Class 60/747)
  • Patent number: 10400672
    Abstract: A cooling system for a fuel injector system of a gas turbine engine has a heat exchanger for cooling a portion of diffuser case air and then routing the cooled diffuser case air through a sleeve that surrounds a fuel injector conduit located in at least the diffuser case plenum for minimizing fuel heat-up rates in the conduit. By minimizing fuel temperatures within the injector conduit, coking accumulation is thereby eliminated or reduced.
    Type: Grant
    Filed: October 31, 2014
    Date of Patent: September 3, 2019
    Assignee: United Technologies Corporation
    Inventors: John D. Frish, Alexander W. Williams, Sean D. Bradshaw
  • Patent number: 10378769
    Abstract: Combustor assemblies having heat shields heat shield attachment features are provided. For example, a combustor assembly includes a dome plate defining first and second apertures, and a heat shield defining first and second openings. The heat shield includes a first cup extending about the first opening and a second cup extending about the second opening. The combustor assembly further includes a collar having a first frame at least partially surrounding the first cup and a second frame at least partially surrounding the second cup. The collar includes a first fastening feature and the dome plate includes a second fastening feature. The first fastening feature mates with the second fastening feature to couple the heat shield to the dome plate. The combustor assembly also may include an attachment piece configured to couple the heat shield to the dome plate. Methods for forming ceramic matrix composite (CMC) heat shields also are provided.
    Type: Grant
    Filed: September 30, 2016
    Date of Patent: August 13, 2019
    Assignee: General Electric Company
    Inventors: Michael Todd Radwanski, Michael Alan Stieg, Donald Michael Corsmeier
  • Patent number: 10378772
    Abstract: Combustor assemblies for gas turbine engines are provided. For example, a combustor assembly comprises a combustor dome, a first heat shield having an edge, a second heat shield having an edge, and a seal extending from the edge of the first heat shield to the edge of the second heat shield such that the seal spans a gap between the first heat shield and the second heat shield. In another embodiment, the seal has a first contact portion contacting the edge of the first heat shield, a second contact portion contacting the edge of the second heat shield edge, and a connecting portion connecting the first portion and the second portion. The first contact portion and the second contact portion project away from the connecting portion. Methods for sealing between adjacent heat shields of a combustor assembly also are provided.
    Type: Grant
    Filed: January 19, 2017
    Date of Patent: August 13, 2019
    Assignee: General Electric Company
    Inventors: Michael Alan Stieg, Valeria Proano Cadena, Aaron Michael Dziech, Michael Todd Radwanski, Donald Michael Corsmeier
  • Patent number: 10215414
    Abstract: A gas turbine system include a first body including a central passage extending from a mixing region to a central outlet at a first downstream end portion of the first body, a fuel outlet in the mixing region, an oxidant outlet in the mixing region, and an outer passage including a first passage extending in a downstream direction toward the first downstream end portion and a second passage extending in an upstream direction from the first downstream end portion into the mixing region.
    Type: Grant
    Filed: April 22, 2015
    Date of Patent: February 26, 2019
    Assignee: General Electric Company
    Inventors: Jeffrey Michael Martini, Gregory Allen Boardman, Bassam Sabry Mohammad Abd El-Nabi, Gerardo Antonio Salazar-Lois
  • Patent number: 10208949
    Abstract: A swirler comprising an anti-rotation feature is provided. The swirler may be installed on a combustor within a gas turbine engine. The swirler may comprise a generally cylindrical profile. In this regard, the swirler may be configured to provide a generally uniform profile within the combustor. The swirler may comprise a floating collar with an anti-rotation feature. The swirler may also include a collar end plate that defines a slot that at least partially encloses the anti-rotation feature and minimizes rotational movement of the floating collar.
    Type: Grant
    Filed: April 12, 2016
    Date of Patent: February 19, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Jonathan J. Eastwood, Jonathan M. Jause
  • Patent number: 10041676
    Abstract: A combustor assembly for a gas turbine engine defining an axial direction is provided. The combustor assembly generally includes a liner, an annular dome, and a deflector plate. The liner at least partially defines a combustion chamber. The annular dome defines a first cavity and has a plurality of impingement holes, and the deflector plate defines a conical surface and a flat surface, wherein a plurality of cooling holes are defined through the deflector plate. The annular dome and the deflector plate are positioned together to define a second cavity that is in fluid communication with the first cavity through the plurality of impingement holes. In addition, the second cavity is in fluid communication with the combustion chamber through the plurality of cooling holes.
    Type: Grant
    Filed: July 8, 2015
    Date of Patent: August 7, 2018
    Assignee: General Electric Company
    Inventors: Nayan Vinodbhai Patel, Kwanwoo Kim, Chad Holden Sutton, Duane Douglas Thomsen, Craig Alan Gonyou, Harris Daniel Abramson, James A. Russo, Robert Andrew Stowers, Shanwu Wang, Anquan Wang
  • Patent number: 10012390
    Abstract: A combustion chamber of a gas turbine having a head plate and a combustion chamber head, where the head plate is connected to the combustion chamber, and where several heat shields arranged in the interior of the combustion chamber are bolted to the head plate, characterized in that each heat shield and the combustion chamber head are fastened to the head plate by means of joint bolted connections.
    Type: Grant
    Filed: July 6, 2015
    Date of Patent: July 3, 2018
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Sebastian Bake, Carsten Clemen
  • Patent number: 9957895
    Abstract: A gas turbine engine is provided that includes a compressor section, a combustor section with a multiple of pre-swirlers, a diffuser case module, and a manifold. The diffuser case module includes a multiple of struts within an annular flow path from said compressor section to said combustor section, wherein at least one of said multiple of struts defines a mid-span pre-diffuser inlet in communication with said annular flow path. The manifold is in communication with said mid-span pre-diffuser inlet and said multiple of pre-swirlers.
    Type: Grant
    Filed: February 28, 2014
    Date of Patent: May 1, 2018
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, William K. Ackermann
  • Patent number: 9874148
    Abstract: There is provided a method for improving the combustion efficiency of a combustor of a gas turbine engine powering an aircraft. The method comprises selectively using two distinct fuel injection units or a combination thereof for spraying fuel in a combustion chamber of the combustor of the gas turbine engine. A first one of the two distinct fuel injection units is selected and optimized for high power demands, whereas a second one of the two distinct fuel injection units is selected and optimized for low power level demands. In operation, the fuel flow ratio between the two distinct injection units is controlled as a function of the power level demand.
    Type: Grant
    Filed: January 31, 2014
    Date of Patent: January 23, 2018
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Bhawan B. Patel, Oleg Morenko
  • Patent number: 9869473
    Abstract: A gas turbine engine combustor conical-flat heat shield includes an annular conical section extending upstream from and being integral with a flat section with a flat downstream facing surface which may be generally perpendicular to or canted with respect to a centerline. The flat section includes radially outer and inner edges at least one of which is circular and circumscribed about a centerline and circumferentially spaced apart clockwise and counter-clockwise radial edges having an origin on the centerline. A gas turbine engine combustor includes conical-flat heat shields in one or more circular rows arranged in a non-symmetrical or asymmetrical pattern. Two or more groups (A, B, C) of the conical-flat heat shields in the circular rows may be mounted on a domeplate and one or more of the conical-flat heat shields is different in one or more of the groups (A, B, C).
    Type: Grant
    Filed: June 25, 2015
    Date of Patent: January 16, 2018
    Assignee: General Electric Company
    Inventors: Ahmed Mostafa Elkady, Allen Michael Danis, Eric Matthew Roberson, Mark Anthony Mueller, George Moertle, Shui-chi Li
  • Patent number: 9534784
    Abstract: A combustor heat shield assembly comprises a circumferential array of heat shield panels individually mounted to an inner surface of a combustor shell. Each heat shield panel has opposed front and back faces, the back face facing the inner surface of the combustor shell and being spaced therefrom to define an air gap. The front and back faces have a perimeter including opposed lateral edges extending between opposed circumferentially extending edges. The lateral edges of adjacent heat shield panels have complementary non-linear profiles defining an asymmetric heat shield panel interface.
    Type: Grant
    Filed: August 23, 2013
    Date of Patent: January 3, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Nigel Caldwell Davenport, Eduardo David Hawie
  • Patent number: 9341376
    Abstract: A combustor includes an end cap having upstream and downstream surfaces and a cap shield surrounding the upstream and downstream surfaces. First and second sets of premixer tubes extend from the upstream surface through the downstream surface. A first fuel conduit supplies fuel to the first set of premixer tubes. A casing circumferentially surrounds the cap shield to define an annular passage, and a second fuel conduit supplies fuel through the annular passage to the second set of premixer tubes. A method for supplying fuel to a combustor includes flowing a working fluid through first and second sets of premixer tubes, flowing a first fuel into the first set of premixer tubes, and flowing a second fuel through an annular passage surrounding the end cap and into the second set of premixer tubes.
    Type: Grant
    Filed: February 20, 2012
    Date of Patent: May 17, 2016
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: James Harold Westmoreland, III, Patrick Benedict Melton
  • Patent number: 9134023
    Abstract: A combustor includes a plurality of tubes arranged in a tube bundle and supported by at least one plate that extends radially within the combustor, wherein each tube includes an upstream end axially separated from a downstream end and provides fluid communication through the tube bundle. A flow conditioner extends upstream from the upstream end of one or more of the plurality of tubes, and a radial passage extends through the flow conditioner. A method for distributing fuel in a combustor including flowing a working fluid through a flow conditioner that extends from a tube that is configured in a tube bundle comprising a plurality of tubes and that is supported by at least one plate. The flow conditioner includes at least one radial passage to impart radial swirl to the working fluid. Flowing a fuel through an annular insert that is at least partially surrounded by the flow conditioner.
    Type: Grant
    Filed: January 6, 2012
    Date of Patent: September 15, 2015
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Gregory Allen Boardman, Geoffrey David Myers, Hasan Karim, Michael John Hughes, Azardokht Hajiloo
  • Patent number: 9127841
    Abstract: 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: Grant
    Filed: March 15, 2010
    Date of Patent: September 8, 2015
    Assignee: SNECMA
    Inventors: Sebastien Alain Christophe Bourgois, Romain Nicolas Lunel, Thomas Olivier Marie Noel
  • Patent number: 9103552
    Abstract: A burner assembly having a fuel distribution ring, number of fuel nozzles which are mounted on the fuel distribution ring in the direction of low is provided. The fuel distribution ring has a ring-shaped surface in the direction of flow and wherein the fuel distribution ring center and an opposite outer outer side and wherein there is at least one slot on the surface between the fuel nozzles and the at least one slot extends on the surface from the outside to the inside. There is at least one recess arranged on the surface and the at least one recess also partially includes the outside of the fuel distributor.
    Type: Grant
    Filed: November 8, 2010
    Date of Patent: August 11, 2015
    Assignee: SIEMENS AKTIENGESELLSCHAFT
    Inventors: Andreas Böttcher, Tobias Krieger, Daniel Vogtmann, Ulrich Wörz
  • Publication number: 20150128601
    Abstract: A gas turbine combustor having a burner including a plurality of fuel nozzles for injecting fuel, air hole plates positioned on a downstream side of the fuel nozzles and a plurality of air holes arranged in pairs with each of the fuel nozzles, and a combustion chamber for mixing fuel injected from the fuel nozzles and air injected from the air holes and injecting and burning the mixed fuel. Each of the fuel nozzles configuring the burners is provided with a projection in which a part of an outer edge of a section of the fuel nozzle is protruded outward; and the projection is arranged so as to be directed toward a center of the gas turbine combustor. The projection of the fuel nozzle is positioned on a downstream side of a flow of combustion air flowing around each of the fuel nozzles.
    Type: Application
    Filed: November 12, 2014
    Publication date: May 14, 2015
    Inventors: Yoshinori MATSUBARA, Keisuke MIURA
  • Patent number: 9003804
    Abstract: A multipoint 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. A plurality of slave injectors are each disposed outward of the master injector for injecting fuel and air in an ignition 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 ignition plumes of the slave injectors. A primary manifold is included within the pressure vessel for distributing fuel to the slave injectors. An auxiliary manifold is in fluid communication with the auxiliary nozzles of the slave injectors for issuing an auxiliary flow of fuel from the auxiliary nozzles that is separate from the fuel flow of the primary manifold.
    Type: Grant
    Filed: October 9, 2012
    Date of Patent: April 14, 2015
    Assignee: Delavan Inc
    Inventor: Lev Alexander Prociw
  • Patent number: 9003802
    Abstract: A fuel injector device for an annular combustion chamber of a turbine engine, including a pilot circuit feeding an injector and a multipoint circuit feeding injection orifices formed in a front face of an annular ring mounted in an annular chamber, together with a thermal insulation mechanism insulating the front face and including an annular cavity formed around the injection orifices between the front face of the annular ring and a front wall of the annular chamber and configured to be filled in operation with air or with coked fuel.
    Type: Grant
    Filed: October 6, 2010
    Date of Patent: April 14, 2015
    Assignee: SNECMA
    Inventors: Didier Hippolyte Hernandez, Emilie Lachaud, Thomas Olivier Marie Noel
  • Patent number: 8978384
    Abstract: A swirler assembly in a gas turbine combustor includes a hub, a shroud, and a plurality of vanes connected between the hub and the shroud. The vanes include a high pressure side on which air and fuel impinge the vanes and a low pressure side. An air circuit is provided in each of the plurality of vanes receiving discharge air from a compressor. Each of the air circuits includes an air entry passage into the vanes and an air exit passage on the low pressure side of the vanes.
    Type: Grant
    Filed: November 23, 2011
    Date of Patent: March 17, 2015
    Assignee: General Electric Company
    Inventors: Donald Mark Bailey, Abdul Rafey Khan, Mohan Krishna Bobba
  • Patent number: 8973369
    Abstract: A gas-turbine burner having a plurality of main swirl generators which each have an inlet flow opening formed by the main swirl generator edge is provided. In order to achieve a uniform flow of combustion air through the main swirl generator, the gas-turbine burner has an inlet-flow guide means with a flow guide surface which runs from one of the inlet-flow openings to an adjacent inlet-flow opening, to which the main swirl generator edges which form the inlet-flow openings are connected, and the flow guide surface widens from there radially upwards. The main swirl generators are central-symmetrically arranged around a pilot burner and the flow guide surface runs radially outside the main swirl generators.
    Type: Grant
    Filed: December 14, 2012
    Date of Patent: March 10, 2015
    Assignee: Siemens Aktiengesellschaft
    Inventors: Robert Angel, Drew Ehlert, Matthias Hase, Michael Huth, James Marshall, Yevgeniy Shteyman
  • Patent number: 8950188
    Abstract: A fuel nozzle assembly for a gas turbine, the assembly including: a cylindrical center body; a cylindrical shroud coaxial with and extending around the center body, and a turning guide having an downstream edge extending in a passage between the center body and an inlet to the shroud, wherein the turning guide extends only partially around the center body.
    Type: Grant
    Filed: September 9, 2011
    Date of Patent: February 10, 2015
    Assignee: General Electric Company
    Inventor: Jason Thurman Stewart
  • Patent number: 8943833
    Abstract: A disclosed fuel injector provides mixing of fuel with airflow by surrounding a swirled fuel flow with first and second swirled airflows that ensures mixing prior to or upon entering the combustion chamber. Fuel tubes produce a central fuel flow along with a central airflow through a plurality of openings to generate the high velocity fuel/air mixture along the axis of the fuel injector in addition to the swirled fuel/air mixture.
    Type: Grant
    Filed: July 6, 2012
    Date of Patent: February 3, 2015
    Assignee: United Technologies Corporation
    Inventors: Richard S. Tuthill, Dustin W. Davis, Zhongtao Dai
  • Patent number: 8938978
    Abstract: A gas turbine engine combustor is provided and includes an array of fuel nozzles, a combustion casing assembly disposed about the array of fuel nozzles and an end cap assembly disposed within the combustion casing assembly to define with the combustion casing assembly an axis-symmetric annulus through which fluid travels into each of the fuel nozzles, at least one of the combustion casing assembly and the end cap assembly being formed with lobed, three-dimensional contouring.
    Type: Grant
    Filed: May 3, 2011
    Date of Patent: January 27, 2015
    Assignee: General Electric Company
    Inventors: Donald Mark Bailey, Jonathan Dwight Berry, Luis Manuel Flamand, Kwanwoo Kim, Patrick Benedict Melton, Robert Joseph Rohrssen, John Drake Vanselow
  • 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: 8919137
    Abstract: An assembly for use in a late lean injection system of a combustor of a combustion turbine engine, wherein the combustor includes an inner radial wall, which defines a primary combustion chamber downstream of a primary fuel nozzle, and an outer radial wall, which surrounds the inner radial wall forming a flow annulus therebetween, the assembly comprising: a boss rigidly secured to the inner radial wall, the boss being configured to define a hollow passageway through the inner radial wall; a transfer tube slideably engaged within the boss; a stop formed on the transfer tube; and damping means positioned between the boss and the stop.
    Type: Grant
    Filed: August 5, 2011
    Date of Patent: December 30, 2014
    Assignee: General Electric Company
    Inventors: Richard Martin DiCintio, Patrick Benedict Melton, Lucas John Stoia
  • Patent number: 8910480
    Abstract: A fuel injector comprises a plurality of swirler vane passages defined between swirler vanes. Each vane is leant with respect to the true radius of the swirler. The pressure distribution through the swirler passages is improved and the flow of air over a prefilmer located at the radially outer edges of the swirl vanes is improved and consequently atomization of fuel is improved and levels of NOx is reduced.
    Type: Grant
    Filed: June 12, 2007
    Date of Patent: December 16, 2014
    Assignee: Rolls-Royce PLC
    Inventors: Federico Suria, Nickolaos Pilatis
  • Publication number: 20140338356
    Abstract: A system including a first multi-tube fuel nozzle including a plurality of first tubes extending in an axial direction, wherein each first tube of the plurality of first tubes includes a first air inlet, a first fuel inlet, and a first fuel-air mixture outlet, a second multi-tube fuel nozzle including a plurality of second tubes extending in an axial direction, wherein each second tube of the plurality of second tubes includes a second air inlet, a second fuel inlet, and a second fuel-air mixture outlet, and an aft plate including a plurality of first tube apertures and a plurality of second tube apertures, wherein the plurality of first tubes extend to the plurality of first tube apertures, and the plurality of second tubes extend to the plurality of second tube apertures.
    Type: Application
    Filed: March 15, 2013
    Publication date: November 20, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventor: GENERAL ELECTRIC COMPANY
  • Publication number: 20140338344
    Abstract: A system including a plurality of multi-tube fuel nozzles each having a plurality of tubes extending in an axial direction, wherein each tube of the plurality of tubes includes an air inlet, a fuel inlet, and a fuel-air mixture outlet, and a fuel nozzle housing, including an outer wall extending circumferentially about a central axis, a plurality of radial walls extending from the outer wall inwardly toward the central axis, a plurality of fuel nozzle receptacles disposed within the outer wall, wherein the plurality of radial walls separate the plurality of fuel nozzle receptacles from one another, and the plurality of multi-tube fuel nozzles are disposed in the plurality of fuel nozzle receptacles a mounting structure including a plurality of radial support arms extending outwardly from the outer wall.
    Type: Application
    Filed: March 15, 2013
    Publication date: November 20, 2014
    Inventors: Jason Thurman Stewart, Christopher Paul Keener, Heath Michael Ostebee
  • Patent number: 8887507
    Abstract: A combustor includes a central fuel nozzle assembly and a plurality of outer fuel nozzle assemblies, each of the plurality of outer fuel nozzle assemblies having a center body and an outer shroud, the plurality of outer fuel nozzle assemblies being configured to abut one another in a surrounding relationship to the central cylinder such that no gaps are present between any two abutting ones of the plurality of outer fuel nozzle assemblies. One or more of the plurality of fuel nozzle assemblies may traverse axially back and forth according to embodiments of the invention.
    Type: Grant
    Filed: April 18, 2012
    Date of Patent: November 18, 2014
    Assignee: General Electric Company
    Inventors: Lewis Berkley Davis, Jr., Joseph Vincent Citeno, Thomas Edward Johnson, Willy Steve Ziminsky
  • Patent number: 8875516
    Abstract: A turbomachine combustor includes a combustion chamber; a plurality of micro-mixer nozzles mounted to an end cover of the combustion chamber, each including a fuel supply pipe affixed to a nozzle body located within the combustion chamber, wherein fuel from the supply pipe mixes with air in the nozzle body prior to discharge into the combustion chamber; and wherein at least some of the nozzle bodies of the plurality of micro-mixer nozzles have axial length dimensions that differ from axial length dimensions of other of the nozzle bodies.
    Type: Grant
    Filed: February 4, 2011
    Date of Patent: November 4, 2014
    Assignee: General Electric Company
    Inventors: Jong Ho Uhm, Baifang Zuo, William David York, Shivakumar Srinivasan
  • Publication number: 20140260271
    Abstract: A system including a plurality of multi-tube fuel nozzles each having a plurality of tubes extending in an axial direction, wherein each tube of the plurality of tubes includes an air inlet, a fuel inlet, and a fuel-air mixture outlet, a fuel nozzle housing including a first outer wall extending circumferentially about a central axis, wherein the plurality of multi-tube fuel nozzles are disposed in the fuel nozzle housing, an inlet flow conditioner removably coupled to a first end portion of the first outer wall, wherein the inlet flow conditioner includes a plurality of air openings, and an aft plate assembly removably coupled to a second end portion of the first outer wall, wherein the aft plate assembly includes an aft plate having a plurality of tube apertures, and the plurality of tubes extend to the plurality of tube apertures.
    Type: Application
    Filed: March 15, 2013
    Publication date: September 18, 2014
    Inventors: Christopher Paul Keener, Jason Thurman Stewart
  • Patent number: 8789372
    Abstract: The system may include a turbine engine. The turbine engine may include a fuel nozzle. The fuel nozzle may include an air path. The fuel nozzle may also include a fuel path such that the fuel nozzle is in communication with a combustion zone of the turbine engine. Furthermore, the fuel nozzle may include a resonator. The resonator may be disposed in the fuel nozzle directly adjacent to the combustion zone.
    Type: Grant
    Filed: July 8, 2009
    Date of Patent: July 29, 2014
    Assignee: General Electric Company
    Inventors: Thomas Edward Johnson, Willy Steve Ziminsky, William David York, Christian Xavier Stevenson
  • 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
  • Patent number: 8756934
    Abstract: A combustor generally includes a shroud that that defines at least one inlet passage extends circumferentially inside the combustor. A first plate extends radially inside the shroud downstream from the inlet passage. The first plate defines at least one inlet port, at least one outlet port and at least partially defines at least one fuel nozzle passage. The shroud at least partially surrounds a sleeve that extends around the fuel nozzle passage. A tube at least partially surrounded by the sleeve may extend through the fuel nozzle passage. The tube, the sleeve, and the first plate may at least partially define an outlet passage. A first fluid flow path generally extends from the at inlet passage to the inlet port, and a second fluid flow path extends generally from the outlet port to the outlet passage.
    Type: Grant
    Filed: October 30, 2012
    Date of Patent: June 24, 2014
    Assignee: General Electric Company
    Inventors: Patrick Benedict Melton, Bryan Wesley Romig, Lucas John Stoia
  • Patent number: 8739543
    Abstract: A method for operating a burner including a burner outlet opening with at least two sectors, each sector is assigned at least one fuel nozzle, is provided. The method is characterized in that fuel is supplied separately to the fuel nozzles of different sectors. Also described is a burner which includes at least two sectors wherein each sector is assigned at least one fuel nozzle. The burner includes at least two separate fuel supply lines and a device for adjusting the fuel mass flow which flows through the respective fuel supply line. The fuel supply lines supply fuel to the fuel nozzles of different sectors. Also described is a gas turbine which is fitted with at least one burner.
    Type: Grant
    Filed: January 18, 2008
    Date of Patent: June 3, 2014
    Assignee: Siemens Aktiengesellschaft
    Inventors: Eberhard Deuker, Anil Gulati, Andreas Heilos
  • 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
  • Patent number: 8733106
    Abstract: An integrated plate is provided for use with a combustor including a casing, a fuel plenum extending circumferentially about the casing, and a fuel nozzle extending axially through the casing. The integrated plate includes a plurality of fuel injection pegs that extend radially between the fuel plenum and the fuel nozzle.
    Type: Grant
    Filed: May 3, 2011
    Date of Patent: May 27, 2014
    Assignee: General Electric Company
    Inventors: Carl Robert Barker, Thomas Edward Johnson, Jonathan Dwight Berry
  • Patent number: 8707671
    Abstract: A fuel control method for a gas turbine with a combustor being formed of at least two groups of a pluralities of main nozzles for supplying fuel, and that supplies fuel from the main nozzles of all groups upon ignition of the combustor (S1), and supplies fuel from three main nozzles of a group A during subsequent acceleration of the gas turbine (S3). Because fuel is injected from a small number of the main nozzles during acceleration, the fuel flow rate per one main nozzle is increased, thereby increasing the fuel-air ratio (fuel flow rate/air flow rate) in a combustion region and improving the combustion characteristics. Accordingly, the generation of carbon monoxide and unburned hydrocarbon is reduced, whereby no bypass valve is required and manufacturing costs are reduced.
    Type: Grant
    Filed: July 1, 2009
    Date of Patent: April 29, 2014
    Assignee: Mitsubishi Heavy Industries, Ltd.
    Inventors: Sosuke Nakamura, Satoshi Tanimura, Shinji Akamatsu, Shinsuke Nakamura, Takashi Sonoda, Akihiko Saito, Makoto Kishi
  • Patent number: 8695348
    Abstract: A combustor of the present invention includes: a plurality of nozzles which is arranged around the central axis of a combustor and of which each base end is connected to an oil supply tube; a nozzle tube base which supports the plurality of nozzles and includes an oil chamber supplying fuel to the nozzles via an oil inflow portion provided in each oil supply tube; a first guide portion which faces the center of the combustor inside the oil chamber and guides the oil remaining inside the oil chamber to the oil inflow portion; and a second guide portion which faces the base end of the combustor inside the oil chamber and guides the oil remaining inside the oil chamber to the oil inflow portion.
    Type: Grant
    Filed: October 27, 2010
    Date of Patent: April 15, 2014
    Assignee: Mitsubishi Heavy Industries, Ltd.
    Inventors: Katsuyoshi Omae, Kenta Taniguchi, Yoshitaka Terada, Takashi Onozuka
  • Patent number: 8666632
    Abstract: A gas turbine engine includes a plurality of fuel injectors grouped operatively by stages in a multistage combustor. A fuel system for the gas turbine engine includes at least one fuel metering module per stage of the multistage combustor. Each fuel metering module includes a pump, a flow meter, a pressure sensor, a controller, and a motor, which work together to control fuel output.
    Type: Grant
    Filed: April 20, 2011
    Date of Patent: March 4, 2014
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Thaddeus J. Zebrowski, Richard E. Versailles
  • Patent number: 8661822
    Abstract: In one embodiment, a system includes a variable geometry resonator configured to couple to a fluid path upstream from a combustor of a turbine engine. The variable geometry resonator is configured to dampen pressure oscillations in the fluid path and the combustor.
    Type: Grant
    Filed: March 2, 2010
    Date of Patent: March 4, 2014
    Assignee: General Electric Company
    Inventors: Ilya Slobodyanskiy, John Lipinski, Shiva Srinivasan, Dmitry Tretyakov
  • Patent number: 8661825
    Abstract: 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: Grant
    Filed: December 17, 2010
    Date of Patent: March 4, 2014
    Assignee: General Electric Company
    Inventors: Divyang Rajendra Desai, Sandeep Gopalakrishna, Kodukulla Venkat Sridhar, Amit Monga
  • Patent number: 8650881
    Abstract: A method for controlling a gas turbine combustion system includes supplying an ultra low calorific fuel to a combustor of the combustion system through a first fuel circuit, controlling a supply of the ultra low calorific fuel through a second fuel circuit as required to control the volumetric flow of the ultra low calorific fuel through the combustor, and combusting the ultra low calorific fuel in the combustor.
    Type: Grant
    Filed: June 30, 2009
    Date of Patent: February 18, 2014
    Assignee: General Electric Company
    Inventors: Willy Steve Ziminsky, Lewis Berkley Davis, Jr.
  • Patent number: 8640463
    Abstract: A swirler for fuel injection in a gas turbine engine includes a frustoconical swirler body. A first and a second air flow path direct air in generally opposed circumferential directions into the swirler. These air paths intermix and create turbulence. As this turbulence encounters fuel droplets, the fuel is atomized, and uniformly distributed within the air flow. A shear layer is created adjacent an inner surface of the swirler body. In a separate feature, a third air flow path is directed into the air.
    Type: Grant
    Filed: June 28, 2011
    Date of Patent: February 4, 2014
    Assignee: United Technologies Corporation
    Inventor: Albert K. Cheung
  • Patent number: 8631656
    Abstract: A gas turbine engine combustor includes an annulus with one or more circular rows of burners and a means for providing a number of equiangular spaced apart flame temperature nonuniformities around the annulus during engine operation. The number of the flame temperature nonuniformities being equal to a circumferential acoustic mode to be attenuated in the combustor (i.e three, five, or seven). Fuel lines and/or water lines in supply communication with the burners and metering orifices in a portion of the fuel lines and/or the water lines may be used to produce the flame temperature nonuniformities. The annulus of the burners may have an equal number of equiangular spaced apart first and second arcuate segments of the burners and a means for operating the burners in the first segments and operating the burners in the second segments at different first and second flame temperatures respectively.
    Type: Grant
    Filed: March 31, 2008
    Date of Patent: January 21, 2014
    Assignee: General Electric Company
    Inventors: Allen Michael Danis, Mark Anthony Mueller, Timothy James Held, Steven Marakovits
  • Patent number: 8607573
    Abstract: 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 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: Grant
    Filed: December 28, 2011
    Date of Patent: December 17, 2013
    Assignee: Hitachi, Ltd.
    Inventors: Keisuke Miura, Hiroshi Inoue, Kazuhito Koyama, Takeo Saito
  • Patent number: 8590311
    Abstract: An improved mixing tube design and fuel nozzle that allows for a more uniform and thorough mixing of fuel and air being fed to the combustor of a gas turbine engine, wherein each of a plurality of mixing tubes comprises a pair of concentric hollow cylinders that define a ring-like, annular path for the flow of fuel between the two hollow cylinders in each mixing tube, a plurality of air injection slots formed in the concentric hollow cylinders defining corresponding air flow paths from the outside into the interior of each mixing tube, and one or more fuel injection ports formed in selected ones of the plurality of air injection slots that allow for the flow of fuel from the annular path formed by the hollow cylinders into the air flow path, resulting in significantly better mixing and improved thermodynamic behavior of the fuel and air mixture downstream of the nozzle and upstream of the combustor.
    Type: Grant
    Filed: April 28, 2010
    Date of Patent: November 26, 2013
    Assignee: General Electric Company
    Inventors: Nishant Govindbhai Parsania, Gregory Allen Boardman
  • Publication number: 20130305739
    Abstract: Certain embodiments include a first individual sector configured to fit together with a plurality of individual sectors to form a combustor cap assembly of a turbine combustor, wherein the first individual sector is configured to fixedly attach to a first fuel nozzle of a plurality of fuel nozzles, the first individual sector comprises a first substantially enclosed cavity configured to surround the first fuel nozzle, and the first substantially enclosed cavity is configured to receive a cooling air flow.
    Type: Application
    Filed: May 18, 2012
    Publication date: November 21, 2013
    Applicant: GENERAL ELECTRIC COMPANY
    Inventor: Jonathan Dwight Berry
  • Publication number: 20130255270
    Abstract: A method and system for providing fuel to primary and secondary fuel nozzles in a gas turbine engine fuel system comprises generating a fuel flow and routing primary fuel from the fuel flow to a primary fuel nozzle. Backpressure on the fuel flow is maintained using a valve. The valve is opened at increased fuel flow to route secondary fuel from the fuel flow to a secondary fuel nozzle. The valve is progressively opened under increasing fuel flows to reduce a pressure drop across the valve produced by the secondary fuel.
    Type: Application
    Filed: March 27, 2012
    Publication date: October 3, 2013
    Applicant: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Kevin Gibbons, Gerald P. Dyer
  • Patent number: 8544276
    Abstract: An object is to provide a low cost gas turbine combustor. The gas turbine combustor has a plurality of main nozzles annularly supported on a nozzle pipe base (11), and the main nozzles each have an oil fuel path for supplying oil fuel and a gas fuel path for supplying gas fuel. A plurality of the oil fuel paths are provided to penetrate the nozzle pipe base (11), and a plurality of lengths of upright piping (21) are provided to be connected to the oil fuel paths, respectively, and be erected on the nozzle pipe base (11). A plurality of lengths of connection piping (22) for interconnecting the lengths of the upright piping (21) in a polygonal shape at a minimum distance are provided outside the nozzle pipe base (11). An oil fuel supply section (14) is connected to one of the lengths of the connection piping (22) to distribute oil fuel to each of the oil fuel paths.
    Type: Grant
    Filed: August 26, 2008
    Date of Patent: October 1, 2013
    Assignee: Mitsubishi Heavy Industries, Ltd.
    Inventors: Yoshitaka Terada, Tetsu Konishi, Katsuyoshi Omae