Injectors In Distinct Radially Spaced Parallel Flow Combustion Products Generators Arranged To Combine Discharges Patents (Class 60/747)
  • Patent number: 11402097
    Abstract: A combustor assembly for a gas turbine engine includes a dome defining a slot. The combustor assembly also includes a liner at least partially defining a combustion chamber and extending between an aft end and a forward end. The forward end is received within the slot of the dome. In one exemplary aspect, the combustor assembly includes features that warm the forward end of the liner during transient operation of the engine. Furthermore, the combustor assembly includes features that reduce the thermal gradient between the forward end and the other portions of the liner. In this way, improved durability of the liner may be achieved.
    Type: Grant
    Filed: January 3, 2018
    Date of Patent: August 2, 2022
    Assignee: General Electric Company
    Inventors: Michael Alan Stieg, Nicholas John Bloom
  • Patent number: 11255270
    Abstract: A fuel injector system includes an outer support and an inner support, with a feed arm extending radially between the inner support and the outer support. A plurality of outlet openings extend in an axial direction from the feed arm for feeding respective injection nozzles. The outer support and feed arm define a plurality of fuel passages therethrough to convey fluid from an external source through the outer support and feed arm to the outlet openings. A heat shield extends around the feed arm from the outer support to the inner support. The heat shield is spaced apart from the feed arm with an insulative gap therebetween.
    Type: Grant
    Filed: December 18, 2018
    Date of Patent: February 22, 2022
    Assignee: Delavan Inc.
    Inventors: Jason A. Ryon, Lev Alexander Prociw, Gregory A. Zink
  • Patent number: 11242993
    Abstract: A combustor provided with: a nozzle having formed therein an air jet section that causes air to be jetted from a nozzle section; a cylindrical part covering the nozzle from the outer peripheral side thereof and forming an air flow path between the cylindrical part and the nozzle; and a pressure loss section provided to the air flow path. The pressure loss section causes a loss of pressure in the air that flows through the air flow path. The nozzle is provided with: at least one air inlet section that takes in air from an outer peripheral surface that is an upstream side from the pressure loss section; and a flow path-forming section forming a discharge air flow path that guides air that is taken in from the at least one air inlet section to the air jet section.
    Type: Grant
    Filed: March 12, 2015
    Date of Patent: February 8, 2022
    Assignee: MITSUBISHI POWER, LTD.
    Inventors: Kei Inoue, Satoshi Takiguchi, Shinji Akamatsu, Kenta Taniguchi, Naoki Abe
  • Patent number: 11175046
    Abstract: A premixer assembly for a combustor includes: at least one ring of premixers, each premixer having a central axis, an annular peripheral wall surrounding a centerbody, and at least one swirler disposed between the centerbody and the peripheral wall, wherein the peripheral wall defines an inlet area of the premixer; and a lip extending forward along the central axis from the peripheral wall, the lip extending at an oblique angle to the axis of symmetry.
    Type: Grant
    Filed: May 9, 2019
    Date of Patent: November 16, 2021
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: David A. Lind, Ajoy Patra, Ting-Yu Tu, Pradeep Naik, Gregory A. Boardman
  • Patent number: 11131457
    Abstract: A combustor includes a combustion chamber; a nozzle supplied with fuel and air to produce a mixed gas of the fuel and the air and configured to inject the mixed gas into the combustion chamber; a fuel supply section coupled to the nozzle casing and configured to supply the fuel to the nozzle; a fuel conditioner that includes a fuel flow path having a serpentine shape and is disposed between the fuel supply section and the nozzle, the fuel conditioner configured to guide the fuel supplied from the fuel supply section to the nozzle along the fuel flow path; and a nozzle casing having an opening into which the nozzle is inserted. The fuel conditioner extends from a first side of the nozzle casing toward a second side. The fuel conditioner and the nozzle casing form a first passage through which fuel may flow to the nozzle.
    Type: Grant
    Filed: August 27, 2019
    Date of Patent: September 28, 2021
    Inventor: Jong Ho Uhm
  • Patent number: 11085637
    Abstract: A gas turbine combustor includes a pilot burner disposed on a central portion of a combustion liner; and a plurality of main burners disposed to surround the pilot burner. The pilot burner includes: a pilot nozzle disposed on the central portion of the combustion liner; and a pilot cone including a widened portion widening downstream away from a downstream end of the pilot nozzle, and an annular portion having an annular shape extending outward in a radial direction from a downstream opening end of the widened portion. The annular portion includes a first position in a circumferential direction and a second position different from the first position in the circumferential direction, and the first position and the second position have different widths in the radial direction.
    Type: Grant
    Filed: March 12, 2019
    Date of Patent: August 10, 2021
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Mitsunori Isono, Keijiro Saito, Shuhei Hosaka
  • Patent number: 11085643
    Abstract: An air swirler arrangement comprises a coaxial arrangement of an inner and an outer air swirler passage. Each air swirler passage comprises a radial flow swirler. Air swirler arrangement comprises a coaxial arrangement of first, second and third members. Second member has radially extending upstream portion spaced axially from first member and a convergent portion. Third member has a radially extending upstream portion spaced axially from the upstream portion of second member and a radially inner surface having convergent and divergent downstream portions and a radially outer surface having a divergent downstream portion. First, second and third members the vanes of the radial flow swirlers is a monolithic structure. Plurality of circumferentially spaced passages are provided within the third member and each passage has an inlet in the surface and an outlet arranged to direct fluid onto the divergent portion of the surface or the surface of the third member.
    Type: Grant
    Filed: January 23, 2019
    Date of Patent: August 10, 2021
    Assignee: ROLLS-ROYCE plc
    Inventors: Richard Freeman, Christopher Rafferty, Thomas Jones, Matthew Murphy, Nicholas M. Brown
  • Patent number: 11015530
    Abstract: A combustor includes a fuel injector to inject fuel; a cooling passage configured to pass compressed air for cooling an outer surface of a liner forming a combustion chamber for containing combustion gas; and a nozzle part that is coupled to the liner and has a rear surface facing the combustion chamber, the nozzle part configured to mix the compressed air with the fuel from the fuel injector and to discharge some of the compressed air in the cooling passage to the rear surface in order to block an introduction of the combustion gas into the nozzle part. Before the compressed air introduced through air introduction holes formed in a nozzle casing is discharged through through-holes formed in a nozzle cap, some of the compressed air may be introduced through bypass holes formed in a bypass tube and then discharged to the combustion chamber through the gap.
    Type: Grant
    Filed: October 14, 2018
    Date of Patent: May 25, 2021
    Inventors: Donggon Lee, Moonsoo Cho
  • Patent number: 10883719
    Abstract: A turbine combustor assembly includes a fuel/air mixer assembly having a plurality of fuel/air mixer elements and a fuel injector coupled to the fuel/air mixer assembly. Each of the fuel/air mixer elements includes: a fuel/air mixer body having an internal cavity extending axially between an air inlet and an air outlet; and a prefilmer residing within an interior cavity of the fuel/air mixer body, the prefilmer including an axial inner air flow passage extending coaxially with an axial centerline of the internal cavity of the fuel/air mixer body and a radial fuel injection port into the air flow passage. The fuel injector is arranged to direct fuel into a plurality of the fuel/air mixer elements via the fuel injection port of the prefilmer of each fuel/air mixer element.
    Type: Grant
    Filed: April 5, 2019
    Date of Patent: January 5, 2021
    Assignee: Woodward, Inc.
    Inventor: Fei Philip Lee
  • Patent number: 10823416
    Abstract: The present disclosure is directed to a combustor assembly for a gas turbine engine comprising a bulkhead wall extended generally along a radial direction relative to a combustor centerline and a mixer disposed concentric to the nozzle centerline. The bulkhead wall defines one or more openings therethrough adjacent to a combustion chamber. Each of the openings defines a nozzle centerline extended along a lengthwise direction. The mixer comprises a retaining wall extended along a radial direction relative to the nozzle centerline and coupled to the upstream side of the bulkhead wall. The mixer further comprises an annular shroud extended at least partially through the one or more openings of the bulkhead wall. The mixer defines a cooling passage through the retaining wall and the annular shroud. The cooling passage defines an inlet opening through the retaining wall and an outlet opening through the annular shroud.
    Type: Grant
    Filed: August 10, 2017
    Date of Patent: November 3, 2020
    Assignee: General Electric Company
    Inventors: Nayan Vinodbhai Patel, Daniel Kirtley, Duane Douglas Thomsen, Neeraj Kumar Mishra, Adam Robert Kahn
  • Patent number: 10739087
    Abstract: An article and method of forming an article are provided. The article includes a body portion separating an inner region and an outer region, an aperture in the body portion, the aperture fluidly connecting the inner region and the outer region, and a baffle extending along at least a portion of an inner surface of the article, the baffle dividing the inner region into a plurality of sub-regions. The method of forming an article includes forming a body portion defining an inner region and an outer region, forming an aperture in the body portion, the aperture fluidly connecting the inner region to the outer region, and forming at least one baffle extending along at least a portion of an inner surface of the body portion, the at least one baffle dividing the inner region into a plurality of sub-regions. Also provided is a component including a cooling article disposed therein.
    Type: Grant
    Filed: September 8, 2015
    Date of Patent: August 11, 2020
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Benjamin Paul Lacy, Sandip Dutta, David Edward Schick
  • Patent number: 10663167
    Abstract: Combustor assemblies are provided. An exemplary combustor assembly comprises an annular ceramic matrix composite (CMC) inner liner including an inner liner flange, an annular CMC outer liner including an outer liner flange, and an annular CMC combustor dome comprising a plurality of tiles positioned circumferentially adjacent one another. Each tile has a first end radially opposite a second end. The CMC inner liner, outer liner, and combustor dome form a combustor, and the CMC combustor dome is positioned at a combustor forward end. The combustor assembly also comprises a support structure for supporting the combustor and including an annular frame having a frame channel defining a groove and an inner and outer support flanges. The first end of each tile is disposed within the frame channel groove. The inner liner flange is secured to the inner support flange and the outer liner flange is secured to the outer support flange.
    Type: Grant
    Filed: June 16, 2017
    Date of Patent: May 26, 2020
    Assignee: General Electric Company
    Inventor: Aaron Michael Dziech
  • Patent number: 10520194
    Abstract: The present disclosure is directed to a radially stacked fuel injection module for a segmented annular combustion system. The fuel injection module includes a bundled tube fuel nozzle portion and a plurality of fuel injection lances. In one instance, a first set of fuel injection lances and a second set of fuel injection lances share a housing with the bundled tube fuel nozzle. The first and second sets of fuel injection lances are radially stacked, each set of lances being in communication with a respective injector fuel plenum. The fuel injection lances deliver fuel to a respective premixing channel formed between the side walls of an integrated combustor nozzle, an aft end of which defines a turbine nozzle. In another instance, the bundled tube fuel nozzle may be provided as a radially inner fuel nozzle and a radially outer fuel nozzle, each with a respective bundled tube fuel plenum.
    Type: Grant
    Filed: March 21, 2017
    Date of Patent: December 31, 2019
    Assignee: General Electric Company
    Inventors: Jonathan Dwight Berry, Michael John Hughes
  • 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: 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: 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: 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: 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
  • 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
  • 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: 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: 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: 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