Fuel And Air Premixed Prior To Combustion Patents (Class 60/737)
  • Patent number: 11143405
    Abstract: The combustor includes a nozzle casing, and combustion nozzles disposed at position spaced apart from each other in the nozzle casing and configured to mix fuel with compressed air and eject the mixture, Where each of the combustion nozzles includes, a nozzle shroud including an inlet through which the compressed air is drawn into the nozzle shroud, and an outlet through which the compressed air is discharged out of the nozzle shroud, an injection cylinder disposed in the nozzle shroud and configured to allow the fuel to be injected into the injection cylinder, and swirlers disposed on an outer circumferential surface of the injection cylinder, where the nozzle shroud includes a region having a constant diameter from the inlet to a predetermined distance along a longitudinal direction of the nozzle shroud.
    Type: Grant
    Filed: October 17, 2018
    Date of Patent: October 12, 2021
    Inventor: Dongsik Han
  • Patent number: 11143407
    Abstract: A combustor a gas turbine engine includes an axial fuel injection system in communication with a combustion chamber, the axial fuel injection system operable to supply between about 10%-35% of a combustion airflow. A radial fuel injection system communicates with the combustion chamber downstream of the axial fuel injection system, where the radial fuel injection system is operable to supply between about 30%-60% of the combustion airflow. A multiple of dilution holes are in communication with a combustion chamber downstream of said radial fuel injection system, where the multiple of dilution holes are operable to supply between about 5%-20% of the combustion airflow.
    Type: Grant
    Filed: June 11, 2014
    Date of Patent: October 12, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: James B. Hoke, Randal G. McKinney, Albert K. Cheung
  • Patent number: 11125437
    Abstract: A method for staging premixers in a combustion system for a gas turbine having a compressor section and a turbine section. The method includes providing a plurality of burners each including premixers wherein compressed air from the compressor section is provided to the premixers. The method also includes providing a plurality of fuel circuits that deliver fuel to the premixers to provide premixed air and fuel used for combustion in the combustion system. In addition, the method includes associating premixers with each fuel circuit in accordance with a power of base two pattern. Further, the method includes activating or deactivating the premixers in stages by activating or deactivating an associated fuel circuit to deliver fuel or stop fuel delivery, respectively, to the premixers wherein a staging step size between consecutive stages is in accordance with a power of base two staging scheme.
    Type: Grant
    Filed: May 16, 2017
    Date of Patent: September 21, 2021
    Assignee: SIEMENS ENERGY GLOBAL GMBH & CO. KG
    Inventors: Marc Furi, Matthew Engelhardt, Fabian Enrique Sanchez, Thomas Scarinci
  • Patent number: 11118512
    Abstract: There is provided a gas turbine (1) including a compressor (2) that generates compressed air, a casing (5) into which the compressed air is introduced, a combustor (3) that generates a combustion gas, a turbine (4) that is driven by the combustion gas, a combustor cooling system (6) that has a sub-compressor (62), which is able to be operated independently of the compressor (2), and a heat exchanger (61), which extracts air in the casing (5) and causes the air to exchange heat after the sub-compressor (62) has increased a pressure of the air, and that introduces the air, which has exchanged heat, into a cooling passage (31) of a cylindrical body (30) of the combustor (3), and a combustor air introducing system that extracts air flowing in the combustor cooling system (6) and introduces the air into the combustor (3).
    Type: Grant
    Filed: March 28, 2017
    Date of Patent: September 14, 2021
    Assignee: MITSUBISHI POWER, LTD.
    Inventors: Kenji Miyamoto, Satoshi Takiguchi, Masakazu Nose
  • Patent number: 11092341
    Abstract: A process includes manufacturing a gas turbine fuel injector body having a stub flange extending radially outward about a circumference of the gas turbine fuel injector body. The stub flange is sized to engage a stepped ledge along a central opening of a mounting flange. The central opening is sized to receive the gas turbine fuel injector body. A gas turbine fuel injector includes a gas turbine fuel injector body and a mounting flange. A method of mounting a gas turbine fuel injector includes placing a stub flange of a gas turbine fuel injector body between a surface of an injector boss and a stepped ledge of a mounting flange. The method also includes securing the gas turbine fuel injector to the injector boss with a plurality of bolts, each bolt extending through a mounting hole in the mounting flange and into a threaded hole in the injector boss.
    Type: Grant
    Filed: January 17, 2017
    Date of Patent: August 17, 2021
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Benjamin Lamar Daniel, Kassy Moy Hart, David William Cihlar, Steven Charles Woods, Jonathan Glenn Reed
  • Patent number: 11085646
    Abstract: A method for controlling pilot-fuel/pilot-air ratio provided to a burner of a combustion system for altering its operating point. First, a value of a first parameter e.g. temperature, is checked, and if the value equals or exceeds a predetermined maximum limit of the first parameter that places the operating point in a first undesired region of operation, then a pilot-fuel/pilot-air ratio is altered such that the value of first parameter is moved to below the first parameter's predetermined maximum limit. Similarly, a value of a second parameter e.g., pressure, is checked, and if the value equals or exceeds a predetermined maximum limit of the second parameter that places the operating point in a second undesired region of operation, then again the pilot-fuel/pilot-air ratio is altered such that the value of second parameter is moved to below the second parameter's predetermined maximum limit. A combustion system operates according to the method.
    Type: Grant
    Filed: September 21, 2017
    Date of Patent: August 10, 2021
    Assignee: SIEMENS ENERGY GLOBAL GMBH & CO. KG
    Inventor: Suresh Sadasivuni
  • Patent number: 11002190
    Abstract: An annular combustion system includes a fuel nozzle, a panel fuel injector including a fuel plenum and at least one premixing channel therein, an inner liner having a hot side surface and a cool side surface and an outer liner having a hot side surface and a cool side surface. The inner liner, the outer liner and the panel fuel injector partially define a hot gas path downstream from the fuel nozzle. The inner liner and/or the outer liner define a plurality of micro-channel cooling passages which is disposed between the hot side surface and cool side surface of the inner liner. Each micro-channel cooling passage of the first plurality of micro-channel cooling passages is in fluid communication with an inlet hole defined along the cool side surface of the respective liner and an outlet hole.
    Type: Grant
    Filed: February 24, 2017
    Date of Patent: May 11, 2021
    Assignee: General Electric Company
    Inventors: Jonathan Dwight Berry, Michael John Hughes
  • Patent number: 10995669
    Abstract: Disclosed herein are a nozzle capable of efficiently atomizing fuel, a combustor, and a gas turbine. The nozzle for the combustor includes a tube assembly including an air passage through which air moves, a main fuel passage disposed inside the air passage so that main fuel moves through the main fuel passage, and a pilot fuel passage disposed inside the main fuel passage so that pilot fuel moves through the pilot fuel passage as well as a nozzle tip configured to eject the pilot fuel and the main fuel, where the nozzle tip includes an injection passage coupled with the pilot fuel passage and a plurality of centrifugal flow chambers disposed outside the injection passage and communicating with the main fuel passage.
    Type: Grant
    Filed: April 24, 2019
    Date of Patent: May 4, 2021
    Inventors: Alexander Myatlev, Hanjin Jeong, Borys Shershnyov
  • Patent number: 10995958
    Abstract: Disclosed are a pilot fuel injector, and a fuel nozzle and a gas turbine having the same. The pilot fuel injector is mounted on the fuel nozzle to uniformize the flow of the introduced air and to enable uniform mixing with the fuel, so that a fuel mixed air having a high mixing rate is provided to the combustion chamber. The mixing rate of the fuel mixed air directed to the combustion chamber is increased, thereby suppressing the generation of nitrogen oxides and preventing the flame stagnation.
    Type: Grant
    Filed: January 15, 2019
    Date of Patent: May 4, 2021
    Inventors: Borys Shershnyov, Yunyoung Doh
  • Patent number: 10995957
    Abstract: A burner for producing a stabilized flame with an inertisation front upstream from the stabilized flame includes a swirl generator and an inlet device with a passage therethrough. The swirl generator swirls an inert process medium about a swirl axis in a flow direction and one or more openings in the inlet device provide one or more partial mass flows containing combustion educts. The inert process medium inhibits combustion of the combustion educts through the inertisation front to displace the stabilized flame from the one or more openings.
    Type: Grant
    Filed: May 8, 2020
    Date of Patent: May 4, 2021
    Assignee: TECHNISCHE UNIVERSITAT BERLIN
    Inventors: Sebastian Schimek, Panagiotis Stathopoulos, Christian Oliver Paschereit
  • Patent number: 10989413
    Abstract: The present disclosure is directed to an axial retention assembly for combustor components of a gas turbine engine. The axial retention assembly may include a combustor having a liner and a casing, with the casing including a flange spaced apart from the liner along an axial centerline of the combustor. Furthermore, the axial retention assembly may include a mounting plate having a first end removably coupled to the flange and a second end positioned inward from the casing in a radial direction. Moreover, the axial retention assembly may include a clamp removably coupled to the liner. Additionally, the axial retention assembly may include a tie rod coupled to the second end of the mounting plate and the clamp to reduce relative movement between the liner and the casing along the axial centerline.
    Type: Grant
    Filed: July 17, 2019
    Date of Patent: April 27, 2021
    Assignee: General Electric Company
    Inventors: Stuart Craig Hanson, Thomas Alan Mogle, II
  • Patent number: 10955134
    Abstract: A fuel burner includes a tube extending from a first end to a second end and including a central passage and fluid directing structure for directing a mixture of air and combustible fuel radially through the tube. The fluid directing structure collectively defines a total flow area. A blocking member is axially movable within the central passage between a first condition blocking a first percentage of the total flow area and a second condition blocking a second percentage of the total flow area different from the first percentage to control the flow of the mixture of air and combustible fuel through the fluid directing structure from the first end to the second end of the tube to be ignited.
    Type: Grant
    Filed: December 27, 2018
    Date of Patent: March 23, 2021
    Assignee: BECKETT GAS, INC.
    Inventor: Michael J. O'Donnell
  • Patent number: 10935243
    Abstract: A liner panel for use in a combustor of a gas turbine engine, the liner panel including a liner panel with a perimeter rail and a multiple of intermediate rails. A combustor for a gas turbine engine including a support shell and a multiple of liner panels mounted to the support shell via a multiple of studs, each of the multiple of liner panels having a multiple of intermediate rails to form a multiple of circumferential cavities.
    Type: Grant
    Filed: November 30, 2016
    Date of Patent: March 2, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Mark F. Zelesky, Randal G. McKinney
  • Patent number: 10920986
    Abstract: A combustor (3) includes a plurality of first burners extending along an axis (P) and arranged at intervals in the circumferential direction, a base plate (31) having support openings configured to support the plurality of first burners and a plurality of through-holes (34) through which base plate air flows toward a downstream side, a plurality of extension pipes supported by the base plate (31) to correspond to the first burners and configured to guide a pre-mixed gas ejected from the first burners toward the downstream side, and a base plate air guide section (35) configured to change a direction of at least some of the base plate air ejected from the through-holes (34) at a downstream side of the base plate (31).
    Type: Grant
    Filed: October 5, 2015
    Date of Patent: February 16, 2021
    Assignee: MITSUBISHI POWER, LTD.
    Inventors: Naoki Tsunoda, Satoshi Takiguchi, Shinji Akamatsu, Taku Egawa, Kenta Taniguchi
  • Patent number: 10883720
    Abstract: A combustion chamber of a turbomachine includes an annular outer casing and a flame tube connected to the outer casing. The flame tube includes an annular inner wall and an annular outer wall defining a first, radial portion at the inlet of the flame tube and a second, axial portion at the outlet of the flame tube. The first portion extends towards the second portion forming an elbow between the inlet and the outlet of the flame tube.
    Type: Grant
    Filed: April 28, 2016
    Date of Patent: January 5, 2021
    Assignee: Safran Aircraft Engines
    Inventors: Guillaume Aurelien Godel, Romain Nicolas Lunel, Thomas Olivier Marie Noel, Matthieu Francois Rullaud
  • Patent number: 10876731
    Abstract: A swirler for mixing fuel with air in a combustion engine includes a central axis, a swirler base with an upper surface, a central portion, a number of main swirler elements and a number of obstruction elements. The main swirler elements and the obstruction elements are located at the upper surface of the swirler base and are arranged around the central portion. The main swirler elements form a number of swirler slots configured for directing a fluid towards the central portion. Each swirler slot has a slot inlet and a slot outlet, wherein the slot outlet is located at a smaller radial distance from the central axis than the swirler inlet. Each obstruction element is located at a slot inlet and configured for forming a plurality of flow channels into the swirler slot.
    Type: Grant
    Filed: April 21, 2017
    Date of Patent: December 29, 2020
    Assignee: SIEMENS AKTIENGESELLSCHAFT
    Inventors: Timothy Dolmansley, James Hird
  • Patent number: 10865991
    Abstract: A combustion apparatus can avoid instability in combustion by controlling a pressure ratio of fuel mixed with air. The combustion apparatus includes a casing; a pilot nozzle disposed at the center of the casing and supplied with fuel by a pilot fuel supply pipe; and a plurality of main nozzles arranged around the pilot nozzle and supplied with fuel by a main fuel supply pipe, each main nozzle including a pair of parallel fuel channels each extending to a respective fuel spray position within the main nozzle. A gas turbine adopting the combustion apparatus includes a plurality of combustors, each combustor including the casing, pilot nozzle, and plurality of main nozzles, with each main nozzle having first and second fuel channels respectively extending to a fuel spray position of the corresponding fuel channel. A pilot manifold connects the respective pilot nozzles, and a main manifold connects the respective main nozzles.
    Type: Grant
    Filed: July 2, 2018
    Date of Patent: December 15, 2020
    Assignee: Doosan Heavy Industries Construction Co., Ltd.
    Inventors: Sung Hyun Kim, Ho Keun Kim, Chea Hong Choi
  • Patent number: 10837639
    Abstract: A burner for a gas turbine engine has a combustion chamber and a swirler adapted to guide a swirler air flow to the combustion chamber, wherein the swirler has a first wall confining the swirler air flow as well as a second wall confining the swirler air flow on the same side as and downstream with respect to the swirler air flow from the first wall and being displaced with respect to the first wall in a direction away from the swirler air flow so that a step being able to cause a flow separation of the swirler air flow is formed by the first wall and the second wall, wherein the second wall has a through hole in its surface adapted to inject a liquid fuel into the swirler air flow.
    Type: Grant
    Filed: June 10, 2016
    Date of Patent: November 17, 2020
    Assignee: Siemens Aktiengesellschaft
    Inventor: Ghenadie Bulat
  • Patent number: 10830441
    Abstract: A swirler is provided for a turbine engine. The swirler includes a swirler housing and a swirler nozzle that is attached to the housing. The housing defines a first inlet and a second inlet. The housing and the nozzle form an inner passage and an outer passage. The inner passage is radially within the nozzle and coupled with the first inlet. The outer passage is radially between the housing and the nozzle and coupled with the second inlet.
    Type: Grant
    Filed: October 1, 2014
    Date of Patent: November 10, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Andreas Sadil, Steven W. Trinks, Jonathan M. Jause
  • Patent number: 10830180
    Abstract: An aft section structure of a jet engine with an axis is comprised of a casing defining a duct around the axis and opened axially fore and aft; a cone tapering aftward at a first angle with the axis and having a pointed end; guide vanes, each of the vanes radially extending from the cone to the casing and comprising a pressure side at a second angle with a plane containing the axis; spray bars, each of the spray bars extending radially within the duct and comprising trailing sides, each of the trailing sides being directed aftward at a third angle with a plane containing the axis; and flame holders, each of the flame holders extending radially within the duct and comprising one or more interior sides, each of the interior sides being directed aftward at a fourth angle with a plane containing the axis.
    Type: Grant
    Filed: August 8, 2017
    Date of Patent: November 10, 2020
    Assignee: IHI Corporation
    Inventors: Shinji Tanaka, Katsuyoshi Takahashi, Jun Hosoi
  • Patent number: 10816209
    Abstract: A fuel injection system may comprise a mixer and a fuel injector disposed within the mixer. The mixer may comprise an outer housing with an exit port and a bluff body extending across the exit port of the outer housing. A flared surface of the mixer may match a contour of the bluff body.
    Type: Grant
    Filed: September 19, 2017
    Date of Patent: October 27, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Albert K. Cheung, James B. Hoke, Randal G. McKinney
  • Patent number: 10794296
    Abstract: The gas turbine combustor and the operation method thereof are designed to minimize visualization of exhaust gas from the gas turbine upon switching of the gas turbine fuel from the oil fuel to the gas fuel. Upon switching of the combustion by the pilot burner from the oil burning to the gas burning, the gas fuel is supplied to the main burners so as to start the gas burning. Then the gas fuel is supplied to the pilot burner to start the gas burning.
    Type: Grant
    Filed: October 23, 2017
    Date of Patent: October 6, 2020
    Assignee: Mitsubishi Hitachi Power Systems, Ltd.
    Inventors: Yasuhiro Akiyama, Mitsuhiro Karishuku, Keita Naito, Kanetsugu Nakamura, Satoshi Dodo, Tomohiro Asai, Yoshitaka Hirata, Akinori Hayashi
  • Patent number: 10788209
    Abstract: A combustor comprises an annular combustor chamber formed between the inner and outer liners. Fuel nozzles each have an end in fluid communication with the annular combustor chamber to inject fuel in the annular combustor chamber, the fuel nozzles oriented to inject fuel in a fuel flow direction having an axial component relative to the central axis of the annular combustor chamber. A plurality of nozzle air holes are defined through the inner liner and the outer liner adjacent to and downstream of the fuel nozzles. The nozzle air holes are configured for high pressure air to be injected from an exterior of the liners through the nozzle air holes generally radially into the annular combustor chamber. A central axis of the nozzle air holes has a tangential component relative to the central axis of the annular combustor chamber.
    Type: Grant
    Filed: August 5, 2015
    Date of Patent: September 29, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Lev Alexander Prociw, Parham Zabeti, Tin Cheung John Hu
  • Patent number: 10774748
    Abstract: A fluid manifold including a manifold body having a first annular passage defined between a first wall of the manifold body and a second wall of the manifold body, wherein the second wall is radially inward from the first wall. A second annular passage is nested radially inward of the firsts annular passage, wherein the second annular passage is defined between the second wall of the manifold body and a third wall of the manifold body radially inward from the second wall of the manifold body.
    Type: Grant
    Filed: January 17, 2017
    Date of Patent: September 15, 2020
    Assignee: Delavan Inc.
    Inventors: Jason A. Ryon, Lev A. Prociw
  • Patent number: 10767556
    Abstract: A method for the combustion of ammonia, wherein a first combustion chamber receives ammonia and hydrogen in controlled proportions, and an oxygen-containing gas. Combustion of the ammonia and hydrogen produces NH2 ions among other combustion products. A second combustion chamber receives the combustion products from the first combustion chamber and receives further ammonia and further hydrogen in controlled proportions, wherein combustion produces nitrogen oxides among other combustion products. A third combustion chamber receives the nitrogen oxides along with further ammonia and further hydrogen in further controlled proportions along with further oxygen-containing gas, such that the nitrogen oxides are combusted into nitrogen and water.
    Type: Grant
    Filed: February 10, 2017
    Date of Patent: September 8, 2020
    Assignee: Siemens Aktiengesellschaft
    Inventors: Ghenadie Bulat, Timothy Hughes, Jonathan May, Ian Wilkinson
  • Patent number: 10738704
    Abstract: A combustor a gas turbine engine includes an axial fuel injection system in communication with a combustion chamber, the axial fuel injection system operable to supply a first percentage of fuel and a radial fuel injection system that communicates with the combustion chamber downstream of the axial fuel injection system, the radial fuel injection system operable to supply a second percentage of fuel, the first percentage and the second percentage of fuel scheduled in response to an engine operating parameter.
    Type: Grant
    Filed: October 3, 2016
    Date of Patent: August 11, 2020
    Assignee: Raytheon Technologies Corporation
    Inventor: William Proscia
  • Patent number: 10739003
    Abstract: An injector of a radial fuel injection system for a combustor of a gas turbine engine includes a swirler; and a fuel nozzle located within the swirler, the fuel nozzle located within the swirler, the fuel nozzle operable to provide a biased radial fuel distribution within the swirler. A method of controlling a fuel flow to a combustor of a gas turbine engine includes selectively controlling a biased radial fuel distribution within a swirler of a radial fuel injection system.
    Type: Grant
    Filed: October 3, 2016
    Date of Patent: August 11, 2020
    Assignee: United Technologies Corporation
    Inventor: William Proscia
  • Patent number: 10738657
    Abstract: A gas turbine facility of an embodiment includes: a combustor casing; a combustor provided in the combustor casing; a cylinder surrounding a periphery of the combustor and dividing a space between the combustor casing and the combustor; a turbine rotated by combustion gas exhausted from the combustor; a heat exchanger cooling the combustion gas exhausted from the turbine; a pipe through which a part of the combustion gas cooled in the heat exchanger passes in the heat exchanger to be heated, the pipe guiding the combustion gas heated in the heat exchanger into the cylinder; and a pipe guiding another part of the combustion gas cooled in the heat exchanger to a space between the combustor casing and the cylinder.
    Type: Grant
    Filed: August 16, 2017
    Date of Patent: August 11, 2020
    Assignee: Toshiba Energy Systems & Solutions Corporation
    Inventors: Yuichi Morisawa, Hideyuki Maeda, Yasuaki Nakamura, Yasunori Iwai, Masao Itoh
  • Patent number: 10731859
    Abstract: A nozzle assembly includes a fuel distributor for issuing a spray of fuel. A fuel conduit is in fluid communication with the fuel distributor and has a first end and a second end. The first end and/or the second end of the fuel conduit is operatively connected to the fuel distributor. The fuel conduit is configured to allow relative movement between the first end and the second end to accommodate dimensional variations of at least one of the nozzle assembly or a combustor. A nozzle system includes the nozzle assembly and a combustor wall having a nozzle inlet. The nozzle assembly is positioned adjacent to the nozzle inlet.
    Type: Grant
    Filed: July 21, 2017
    Date of Patent: August 4, 2020
    Assignee: Delavan Inc.
    Inventors: Lev A. Prociw, Jason A. Ryon, Gregory A. Zink
  • Patent number: 10724441
    Abstract: An annular combustion system includes a fuel nozzle, a panel fuel injector including a fuel plenum and at least one premixing channel therein, an inner liner including an inner band radially spaced from an outer band and an inner flow annulus formed therebetween, and an outer liner radially spaced from the inner liner and comprising an inner band radially spaced from an outer band and an outer flow annulus formed therebetween. The fuel nozzle is positioned radially between the inner liner and the outer liner, and the panel fuel injector extends radially between the inner liner and the outer liner. At least one of the inner flow passage and the outer flow passage is in fluid communication with at least one of a premix air plenum, a cooling air cavity and a cooling air plenum defined within the panel fuel injector.
    Type: Grant
    Filed: February 24, 2017
    Date of Patent: July 28, 2020
    Assignee: General Electric Company
    Inventors: Jonathan Dwight Berry, Michael John Hughes
  • Patent number: 10712009
    Abstract: A burner head for a burner defines a burner longitudinal axis along which the burner extends. The burner head includes a base body and at least one oxidant duct defining a duct longitudinal axis. The oxidant duct is arranged in the base body at a radial spacing to the burner longitudinal axis. A fuel duct body is inserted into the oxidant duct and at least one fuel nozzle is configured on the fuel duct body so as to open into the oxidant duct.
    Type: Grant
    Filed: March 27, 2017
    Date of Patent: July 14, 2020
    Assignee: Duerr Systems AG
    Inventors: Thomas Baumann, Axel Widenhorn
  • Patent number: 10704787
    Abstract: A closed trapped vortex apparatus includes: a tubular structure having a structural wall, the structural wall forming a cavity within the tubular structure, the structural wall having a lower boundary wall forming a boundary between the cavity and a core flow passage; at least one driver hole passing through the structural wall; an ignition source communicating with the cavity; a fuel source communicating with the cavity; and a plurality of flame tubes extending through the lower boundary wall of the tubular structure at preselected locations so as to provide communication between the cavity and the core flow passage.
    Type: Grant
    Filed: March 30, 2016
    Date of Patent: July 7, 2020
    Assignee: General Electric Company
    Inventor: David Andrew Perveiler
  • Patent number: 10690350
    Abstract: A combustor with axially staged fuel injection includes a plurality of nozzle segments annularly arranged about a center fuel nozzle. Each nozzle segment includes a fuel plenum partially defined between a forward plate and an aft plate and a plurality of tubes that extends through the fuel plenum and the aft plate. A panel fuel injector extends axially downstream from the aft plate and includes an outer wall, an inner wall, a plurality of outlets defined along at least one of the outer wall and the inner wall and a plurality of premix channels defined between the outer wall and the inner wall. Each premix channel is in fluid communication with a fuel supply, a compressed air supply and a respective outlet of the plurality of outlets.
    Type: Grant
    Filed: November 28, 2016
    Date of Patent: June 23, 2020
    Assignee: GENERAL ELECTRIC COMPANY
    Inventor: Jonathan Dwight Berry
  • Patent number: 10684018
    Abstract: An annular combustion chamber with an axis of revolution of a turbine engine delimited by coaxial inner and outer annular walls joined upstream by a substantially transverse bottom of the chamber, the chamber further comprising at least one annular deflector placed in the chamber and substantially parallel to the bottom of the chamber the bottom of the chamber having orifices designed to be passed through by the impact cooling air of the deflector and coming from upstream. The deflector is attached to the inner and outer walls in a sealed manner, and the cooling air of the deflector is discharged from the chamber through exhaust holes formed in the inner and outer walls.
    Type: Grant
    Filed: March 8, 2018
    Date of Patent: June 16, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Patrice André Commaret, Romain Nicolas Lunel
  • Patent number: 10677466
    Abstract: A combustor includes an inlet flow conditioner. The inlet flow conditioner includes a sleeve that circumferentially surrounds a portion of a fuel nozzle assembly and that extends from a forward end of a combustion liner to an inner surface of an end cover. The sleeve defines a plurality of apertures circumferentially spaced about the sleeve. A portion of the inner surface of the end cover and the sleeve define a head end volume of the combustor. An inlet to a premix passage of at least one fuel nozzle of the fuel nozzle assembly is disposed within and is in fluid communication with the head end volume.
    Type: Grant
    Filed: October 13, 2016
    Date of Patent: June 9, 2020
    Assignee: General Electric Company
    Inventors: Jonathan Dwight Berry, Brandon Lamar Bush, Timothy James Purcell, Lucas John Stoia
  • Patent number: 10655857
    Abstract: A gas turbine engine combustion chamber includes upstream and downstream ring structures and a plurality of circumferentially arranged combustion chamber segments. Each segment extends the full length of the combustion chamber and each segment is secured to the upstream ring structure and is mounted on the downstream ring structure. The upstream end of each combustion chamber segment includes a surface having a plurality of circumferentially spaced radially extending holes and the upstream ring structure having a plurality of circumferentially spaced holes extending radially through a portion abutting the surface of the upstream end of each combustion chamber segment. Each combustion chamber segment being removably secured to the upstream ring structure by a plurality of fasteners locatable in the holes in the combustion chamber segment and corresponding holes in the upstream ring structure.
    Type: Grant
    Filed: June 29, 2017
    Date of Patent: May 19, 2020
    Assignee: ROLLS-ROYCE PLC
    Inventors: Stephen C Harding, Paul A Hucker
  • Patent number: 10655858
    Abstract: The present disclosure provides assemblies for cooling a liquid fuel cartridge unit within a combustor head end. In one embodiment, the cooling is accomplished passively as air from the head end air plenum is directed into a cooling channel radially outward of a liquid fuel delivery conduit. In another embodiment, the cooling of the liquid fuel cartridge unit is accomplished actively as air is directed through a first air flow conduit radially inward of the liquid fuel delivery conduit and then redirected through a second air flow conduit radially outward of the liquid fuel delivery conduit.
    Type: Grant
    Filed: June 16, 2017
    Date of Patent: May 19, 2020
    Assignee: General Electric Company
    Inventors: Donald Mark Bailey, Lucas John Stoia, Timothy James Purcell
  • Patent number: 10648672
    Abstract: An apparatus and method for assisting with the combustion of fuel are described. The apparatus includes a swirler assembly and a fuel nozzle. Fuel is directed into a fuel nozzle mixing chamber and combines with air therein to form a fuel-air mixture. At least one plasma generator, at least partially within the fuel nozzle, generates an at least one of an at least partially ionized air-fuel mixture and an at least partially dissociated air-fuel mixture (“at least partially I/D air-fuel mixture”) via a plasma generator discharge. A combustion chamber inlet admits the at least partially I/D air-fuel mixture from the plasma generator into a combustion chamber internal volume. Combustion air flows through the swirler body and into the combustion chamber internal volume. Combustion of the at least partially I/D air-fuel mixture with the combustion air occurs at least partially within the combustion chamber internal volume to responsively produce products.
    Type: Grant
    Filed: August 18, 2016
    Date of Patent: May 12, 2020
    Assignee: FGC PLASMA SOLUTIONS LLC
    Inventor: Felipe Gomez del Campo
  • Patent number: 10634344
    Abstract: A fuel nozzle assembly includes a flange body including a stem. The flange body defines a flow passage therethrough. The fuel nozzle assembly further includes a conduit assembly having an inner tube that is disposed within an outer tube. A purge passage is defined radially between the inner tube and the outer tube and a fuel passage is defined within the inner tube. The outer tube and the inner tube are connected to the stem with the inner tube being connected to the stem via a flexible coupling disposed within the purge passage. The purge passage is in fluid communication with an inlet flow plenum and with a plurality of premix tubes of the fuel nozzle assembly.
    Type: Grant
    Filed: December 20, 2016
    Date of Patent: April 28, 2020
    Assignee: General Electric Company
    Inventors: Donald Mark Bailey, Lucas John Stoia
  • Patent number: 10634355
    Abstract: A nozzle includes a nozzle body defining a longitudinal axis. The nozzle body includes an inner air passage fed by a radial swirler and having a converging conical cross-section. A first fuel circuit is radially outboard from the air passage with respect to the longitudinal axis. A second fuel circuit is radially outboard from the first fuel circuit with respect to the longitudinal axis, wherein each of the first fuel circuit and the second fuel circuit extends from a respective fuel circuit inlet to a respective annular fuel circuit outlet. An outer air passage is defined between a fuel circuit outer wall and an outer air passage wall, wherein the outer air passage is a converging non-swirling outer air passage.
    Type: Grant
    Filed: December 16, 2016
    Date of Patent: April 28, 2020
    Assignee: Delavan Inc.
    Inventors: Lev Alexander Prociw, Jason A. Ryon
  • Patent number: 10612784
    Abstract: The present disclosure is directed to a nozzle assembly including a header manifold and a ring manifold, which defines a liquid fuel plenum, spaced from the header manifold. An outer sleeve connects to the ring manifold, and a nozzle body connects to the outer sleeve. The ring manifold, the outer sleeve, and the nozzle body define a fluid chamber. An inner fuel tube extends from the header manifold to the nozzle body. A portion of the inner fuel tube extends helically about an axial centerline of the nozzle assembly between the ring manifold and the nozzle body. A first fuel tube extends helically around a portion of the inner fuel tube. The first fuel tube fluidly couples the liquid fuel plenum to the header manifold. A second fuel tube extends helically around a portion of the inner fuel tube and fluidly couples the liquid fuel plenum to the header manifold.
    Type: Grant
    Filed: June 19, 2017
    Date of Patent: April 7, 2020
    Assignee: General Electric Company
    Inventors: Kaitlin Marie Graham, Thomas Edward Johnson, Geoffrey David Myers
  • Patent number: 10605169
    Abstract: Combustor panels for use in gas turbine engine combustors having a panel body having a peripheral rail around a periphery of the panel body, a first boss formed on the panel body and surrounding a first aperture that passes through the panel body, and a first webbing that extends from the peripheral rail toward the first boss. A first annular channel is formed between the first webbing and the first boss and surrounds the first boss and a first web pocket is formed within the first webbing between the peripheral rail and the first boss and defines a local extension of the first annular channel extending from the first boss to the peripheral rail.
    Type: Grant
    Filed: April 18, 2017
    Date of Patent: March 31, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Dennis M. Moura, James B. Hoke, Reza Rezvani
  • Patent number: 10590850
    Abstract: A burner injects a mixture of fuel and air from a base end side far from a combustion chamber toward a distal end side close to the combustion chamber. The burner has a fuel passage having a turn-back part turning back and channeling the fuel between the base end side and the distal end side. The burner has a premixed gas passage formed to surround the fuel passage. The burner has a fuel introduction part introducing the fuel channeled through the fuel passage into the premixed gas passage from the base end side to the distal end side. The burner has an air supply part supplying the premixed gas passage with air on the base end side.
    Type: Grant
    Filed: November 4, 2015
    Date of Patent: March 17, 2020
    Assignee: KAWASAKI JUKOGYO KABUSHIKI KAISHA
    Inventors: Masahiro Ogata, Takeo Oda, Yasuhiro Kinoshita, Kohshi Hirano, Takahiro Uto
  • Patent number: 10584638
    Abstract: The present disclosure is directed to a combustion system including a panel fuel injector. The panel fuel injector includes a first side wall, a second side wall, and an aft wall. The first side wall and the second side wall are interconnected by the aft wall. The panel fuel injector further includes a cooling air plenum that is defined between the first side wall and the second side wall. The aft wall defines a plurality of cooling holes in fluid communication with the cooling air plenum. One or more of the cooling holes of the plurality of cooling holes is oriented towards at least one of a leading edge, a pressure side wall, or a suction side wall of a stationary nozzle disposed proximate to the aft end wall.
    Type: Grant
    Filed: February 24, 2017
    Date of Patent: March 10, 2020
    Assignee: General Electric Company
    Inventors: Jonathan Dwight Berry, Michael John Hughes
  • Patent number: 10578021
    Abstract: A combustion system for a gas turbine engine includes a combustor dome. The combustor dome includes a fuel manifold with an inlet and nozzle components of a plurality of nozzles circumferentially spaced around the combustor dome. The fuel manifold and nozzle components are integrated with the combustor dome for fluid communication from the inlet to the nozzle components.
    Type: Grant
    Filed: June 26, 2015
    Date of Patent: March 3, 2020
    Assignee: Delavan Inc
    Inventor: Lev A. Prociw
  • Patent number: 10570826
    Abstract: A fluid manifold includes a manifold body, a first annular passage and a second annular passage. The first annular passage is defined within the manifold body between a first passage inlet and a first passage outlet downstream from the first passage inlet. The second annular passage is defined within the manifold body nested radially outward from the first annular passage, and between a second passage inlet and a second passage outlet downstream from the second passage inlet. The first and second annular passages are concentric about a manifold axis. The first passage outlet and the second passage outlet are positioned at the same axial position relative to the manifold axis.
    Type: Grant
    Filed: September 25, 2017
    Date of Patent: February 25, 2020
    Assignee: Delavan Inc.
    Inventors: Jason A. Ryon, Jacob Greenfield, Lev Alexander Prociw
  • Patent number: 10557634
    Abstract: 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: Grant
    Filed: November 3, 2008
    Date of Patent: February 11, 2020
    Assignee: MAN Energy Solutions SE
    Inventors: Eric Norster, Holger Huitenga, Reiner Brinkmann
  • Patent number: 10527286
    Abstract: A nozzle includes a nozzle body with an inner air passage fed by a first radial swirler and a second radial swirler axially downstream of the first radial swirler. A first fuel circuit is axially between the first and second radial swirlers. A second fuel circuit is axially downstream of the second radial swirler, wherein each of the first fuel circuit and the second fuel circuit extends from a respective fuel circuit inlet to a respective annular fuel circuit outlet. An outer air passage is defined between a fuel circuit outer wall of the second fuel circuit and an outer air passage wall, wherein the outer air passage is a converging non-swirling air passage. An intermediate air passage can be defined between an intermediate wall and the second radial swirler, wherein the intermediate air passage is a converging non-swirling air passage.
    Type: Grant
    Filed: December 16, 2016
    Date of Patent: January 7, 2020
    Assignee: DELAVAN, INC
    Inventors: Lev Alexander Prociw, Jason A. Ryon
  • Patent number: 10508811
    Abstract: An injector of a radial fuel injection system for a combustor of a gas turbine engine includes a swirler; and a fuel nozzle located within the swirler, the fuel nozzle located within the swirler, the fuel nozzle operable to provide a biased circumferential fuel distribution within the swirler. A method of controlling a fuel flow to a combustor of a gas turbine engine includes selectively controlling a biased circumferential fuel distribution within a swirler of a radial fuel injection system.
    Type: Grant
    Filed: October 3, 2016
    Date of Patent: December 17, 2019
    Assignee: United Technologies Corporation
    Inventor: William Proscia
  • Patent number: 10508600
    Abstract: A retaining bracket is attached to a fuel nozzle for cooperating with a flange on a fuel transfer tube to prevent the fuel transfer tube from becoming disconnected from the fuel nozzle during engine operation. The retaining bracket is shaped so as to form an enclosure over a head of the nozzle, the enclosure acting as a fire shield to allow the nozzle to perform its intended functions for a predetermined period of time when exposed to an engine fire event.
    Type: Grant
    Filed: May 27, 2016
    Date of Patent: December 17, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Oleg Morenko