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公开(公告)号：US11226101B2
公开(公告)日：2022-01-18
申请号：US16264775
申请日：2019-02-01
Applicant: General Electric Company
Inventor： Karthikeyan Sampath , Saket Singh , Gurunath Gandikota , Perumallu Vukanti , Pradeep Naik , Steven Clayton Vise
Abstract: A gas turbine engine swirler that includes a tubular body having a forward face, an aft end, and a throat. A plurality of primary swirl vanes that is positioned between the aft end and the forward face. A plurality of secondary swirl vanes that is positioned between the primary swirl vanes and the aft end. The plurality of primary swirl vanes and the plurality of secondary swirl vanes are configured such that the throat is fluidly connected to a plenum that is positioned outside of the tubular body. A tubular ferrule is positioned such that it joins the body at the forward face thereof. Each of the primary swirl vanes extend radially inwardly to a vane lip. The secondary swirl vanes extend radially inwardly for swirling air therefrom. The body also includes a tubular Venturi that extends aft from between the primary swirler vanes and the secondary swirler vanes for radially separating air swirled therefrom. Wherein the primary swirl vanes are configured to swirl air along a passageway and through an outlet that is oriented axially aft.
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公开(公告)号：US11156360B2
公开(公告)日：2021-10-26
申请号：US16278341
申请日：2019-02-18
Applicant: General Electric Company
Abstract: A fuel nozzle for a gas turbine engine is generally provided. The fuel nozzle includes an outer sleeve extended circumferentially around a fuel nozzle centerline and extended along a longitudinal direction co-directional to the fuel nozzle centerline. The outer sleeve defines a plurality of first radially oriented air inlet ports through the outer sleeve in circumferential arrangement relative to the fuel nozzle centerline. A centerbody is positioned radially inward of the outer sleeve. The centerbody includes an outer annular wall extended circumferentially around the fuel nozzle centerline and extended along the longitudinal direction co-directional to the fuel nozzle centerline. The outer sleeve further includes a first radial wall extended from a downstream end of the outer annular wall. The centerbody defines a plenum radially inward thereof. The outer annular wall and the outer sleeve together define a first fuel air mixing passage extended along the longitudinal direction therebetween. A fuel injector is disposed in the plenum. The fuel injector includes a tubular outer wall extended co-directional to the fuel nozzle centerline. The outer wall defines a second fuel air mixing passage therewithin. The second fuel air mixing passage is extended through the first radial wall of the centerbody.
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公开(公告)号：US11067280B2
公开(公告)日：2021-07-20
申请号：US16375958
申请日：2019-04-05
Applicant: General Electric Company
Inventor： Gregory Allen Boardman , Pradeep Naik , Manampathy Gangadharan Giridharan , David Albin Lind , Jeffrey Michael Martini
Abstract: The present disclosure is directed to a method for operating a turbine engine, the method including arranging a fluid conduit through a fuel nozzle in a first direction toward a downstream end and in a second direction toward an upstream end, the fluid conduit in fluid communication with a premix passage via a fluid injection port; flowing an oxidizer into the premix passage via a radially oriented first inlet port and a radially oriented second inlet port; flowing a first fuel to the premix passage through the fluid conduit and the fluid injection port, wherein the first fuel is provided to the premix passage axially downstream of the first inlet port; and generating a premixed flame from a mixture of the oxidizer and the first fuel.
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公开(公告)号：US10935245B2
公开(公告)日：2021-03-02
申请号：US16196383
申请日：2018-11-20
Applicant: General Electric Company
Inventor： Gregory Allen Boardman , Manampathy Gangadharan Giridharan , Michael Anthony Benjamin , Pradeep Naik , Clayton Stuart Cooper , Vishal Sanjay Kediya
Abstract: A fuel nozzle for a gas turbine engine is generally provided. The fuel nozzle includes an outer sleeve extended circumferentially around a fuel nozzle centerline and extended along a longitudinal direction substantially co-directional to the fuel nozzle centerline. The outer sleeve defines a plurality of first radially oriented air inlet ports through the outer sleeve in circumferential arrangement relative to the fuel nozzle centerline. The fuel nozzle further includes a centerbody positioned radially inward of the outer sleeve. The centerbody is extended along the longitudinal direction substantially co-directional to the fuel nozzle centerline and wherein the centerbody is concentric to the fuel nozzle centerline and the outer sleeve. The centerbody defines a plurality of second radially oriented air inlet ports through the centerbody in circumferential arrangement relative to the fuel nozzle centerline. The centerbody further defines an annular centerbody groove or depression relative to the fuel nozzle centerline at a downstream end directly adjacent to a combustion chamber. The fuel nozzle further includes an inner sleeve extended circumferentially around the fuel nozzle centerline and extended along the longitudinal direction substantially co-directional to the fuel nozzle centerline. The inner sleeve is positioned radially between the outer sleeve and the centerbody. The inner sleeve further defines an annular inner sleeve depression relative to the fuel nozzle centerline at the downstream end directly adjacent to the combustion chamber. The outer sleeve and the inner sleeve together define a first fuel air mixing passage radially therebetween and extended substantially along the longitudinal direction in direct fluid communication with the combustion chamber. The inner sleeve and the centerbody together further define a second fuel air mixing passage radially therebetween and extended substantially along the longitudinal direction in direct fluid communication with the combustion chamber.
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公开(公告)号：US20200158343A1
公开(公告)日：2020-05-21
申请号：US16196383
申请日：2018-11-20
Applicant: General Electric Company
Inventor： Gregory Allen Boardman , Manampathy Gangadharan Giridharan , Michael Anthony Benjamin , Pradeep Naik , Clayton Stuart Cooper , Vishal Sanjay Kediya
Abstract: A fuel nozzle for a gas turbine engine is generally provided. The fuel nozzle includes an outer sleeve extended circumferentially around a fuel nozzle centerline and extended along a longitudinal direction substantially co-directional to the fuel nozzle centerline. The outer sleeve defines a plurality of first radially oriented air inlet ports through the outer sleeve in circumferential arrangement relative to the fuel nozzle centerline. The fuel nozzle further includes a centerbody positioned radially inward of the outer sleeve. The centerbody is extended along the longitudinal direction substantially co-directional to the fuel nozzle centerline and wherein the centerbody is concentric to the fuel nozzle centerline and the outer sleeve. The centerbody defines a plurality of second radially oriented air inlet ports through the centerbody in circumferential arrangement relative to the fuel nozzle centerline. The centerbody further defines an annular centerbody groove or depression relative to the fuel nozzle centerline at a downstream end directly adjacent to a combustion chamber. The fuel nozzle further includes an inner sleeve extended circumferentially around the fuel nozzle centerline and extended along the longitudinal direction substantially co-directional to the fuel nozzle centerline. The inner sleeve is positioned radially between the outer sleeve and the centerbody. The inner sleeve further defines an annular inner sleeve depression relative to the fuel nozzle centerline at the downstream end directly adjacent to the combustion chamber. The outer sleeve and the inner sleeve together define a first fuel air mixing passage radially therebetween and extended substantially along the longitudinal direction in direct fluid communication with the combustion chamber. The inner sleeve and the centerbody together further define a second fuel air mixing passage radially therebetween and extended substantially along the longitudinal direction in direct fluid communication with the combustion chamber.
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Patent Agency Ranking
公开(公告)号：US20190120493A1
公开(公告)日：2019-04-25
申请号：US15793129
申请日：2017-10-25
Applicant: General Electric Company
Inventor： Gregory Allen Boardman , Pradeep Naik , Joseph Zelina , Clayton Stuart Cooper
Abstract: A combustor assembly is generally provided. The combustor assembly includes a volute wall extended annularly around a combustor centerline, an annular inner wall extended at least partially along a lengthwise direction from the volute wall, and an annular outer wall extended at least partially along the lengthwise direction from the volute wall. The volute wall is extended at least partially as a spiral curve from a circumferential reference line around the combustor centerline and defines a combustion chamber within the volute wall. The inner wall and the outer wall are separated along a radial direction from the combustor centerline. A primary flow passage is defined between the inner wall and the outer wall in fluid communication from the combustion chamber. A flow passage wall is extended to a portion of the volute wall and a portion of the outer wall. The flow passage wall defines a secondary flow passage and a tertiary flow passage between the volute wall, the outer wall, and the flow passage wall. The secondary flow passage and the tertiary flow passage are each in adjacent circumferential arrangement of one another around the combustor centerline. The volute wall and the outer wall together define one or more secondary outlet openings adjacent to the combustion chamber and in fluid communication with the combustion chamber. The outer wall defines one or more tertiary outlet openings in fluid communication with the tertiary flow passage and the primary flow passage.
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公开(公告)号：US20180128490A1
公开(公告)日：2018-05-10
申请号：US15343634
申请日：2016-11-04
Applicant: General Electric Company
Inventor： Gregory Allen Boardman , Pradeep Naik , Manampathy Gangadharan Giridharan , David Albin Lind , Jeffrey Michael Martini , Clayton S. Cooper
CPC classification number: F23R3/286 , F23R3/04 , F23R3/14 , F23R3/283 , Y02T50/675
Abstract: The present disclosure is directed to a fuel injector for a gas turbine engine. The fuel injector includes an end wall, a centerbody, an outer sleeve surrounding the centerbody from the end wall toward the downstream end of the fuel injector, and a thermal management conduit. The centerbody includes an axially extended outer wall and inner wall extended from the end wall toward a downstream end of the fuel injector. The outer wall, the inner wall, and the end wall together define a fluid conduit extended in a first direction toward the downstream end of the fuel injector and in a second direction toward an upstream end of the fuel injector. The outer sleeve and the centerbody define a premix passage radially therebetween and an outlet at the downstream end of the premix passage. The outer sleeve defines a plurality of radially oriented first air inlet ports in circumferential arrangement at a first axial portion of the outer sleeve. The outer sleeve defines a plurality of radially oriented second air inlet ports in circumferential arrangement at a second axial portion of the outer sleeve. The outer sleeve further defines a first fluid passage arranged between each first air inlet port and extended from the end wall. A fluid passage wall extends from the end wall within the first fluid passage to define a second fluid passage extended from the end wall within the first fluid passage. The outer sleeve further defines a first injection port in fluid communication with the first fluid passage and a second injection port in fluid communication with the second fluid passage. The thermal management conduit is defined by the fluid communication of the fluid conduit and the first fluid passage and the thermal communication of the second fluid passage in adjacent arrangement with the first fluid passage.
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公开(公告)号：US20170067635A1
公开(公告)日：2017-03-09
申请号：US14849552
申请日：2015-09-09
Applicant: General Electric Company
Inventor： Nan Zong , Ahmed Mostafa ELKady , Mark Anthony Mueller , Pradeep Naik , Gerardo Antonio Salazar Lois , Rishikesh Prakash Karande , Jeffrey Michael Martini
CPC classification number: F23R3/002 , F04D29/542 , F23R3/04 , F23R3/10 , F23R3/28 , F23R3/44 , F23R3/46 , F23R3/50 , F23R3/54 , Y02T50/675
Abstract: A system including an annular combustor having a first liner wall disposed circumferentially about an axis, a combustion chamber disposed circumferentially about the first liner wall, and a second liner wall disposed circumferentially about the combustion chamber. The annular combustor is configured to direct a combustion gas flow in a downstream direction through the combustion chamber away from a head end toward a turbine. The system also includes a supply passage configured to supply a fluid flow from a compressor to the combustion chamber. The supply passage has a flow path architecture having a turning portion that turns the fluid flow from a compressor discharge direction to an upstream direction generally opposite the downstream direction of combustion gas flow.
Abstract translation: 一种包括环形燃烧器的系统，其具有围绕轴线周向设置的第一衬套壁，围绕第一衬里壁周向设置的燃烧室和围绕燃烧室周向设置的第二衬套壁。 环形燃烧器被配置成将下游方向的燃烧气体流引导通过燃烧室远离头端朝向涡轮机。 该系统还包括供应通道，其构造成将来自压缩机的流体流供应到燃烧室。 供给通道具有流路结构，其具有将流体流从压缩机排出方向转动到与燃烧气体流动的下游方向大致相反的上游侧的转向部。
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公开(公告)号：US20250123001A1
公开(公告)日：2025-04-17
申请号：US18967923
申请日：2024-12-04
Applicant: General Electric Company
Inventor： Ranjeet Kumar Mishra , Jayanth Sekar , Pradeep Naik , Gregory A. Boardman , Randall C. Boehm
Abstract: A premixer for a combustor includes: a centerbody having a hollow interior cavity; a swirler assembly radially outward of the centerbody; a peripheral wall disposed radially outward of the centerbody and the swirler assembly such that a mixing duct is defined between the peripheral wall and the centerbody, downstream from the swirler assembly; an annular splitter radially inward of the swirler assembly and radially outward of the centerbody such that a radial gap is defined between the splitter and an outer surface of the centerbody, wherein the splitter includes a trailing edge which extends axially aft of the swirler assembly; a fuel gallery disposed inside the interior cavity of the centerbody; and at least one fuel injector extending outward from the fuel gallery and passing through an injector port communicating with the outer surface of the splitter.
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公开(公告)号：US20250116402A1
公开(公告)日：2025-04-10
申请号：US18768665
申请日：2024-07-10
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Aritra Chakraborty , Perumallu Vukanti , Pradeep Naik , Arijit Sinha Roy , Bhavya Naidu Panduri , R. Narasimha Chiranthan , Ajoy Patra , Michael T. Bucaro , Sibtosh Pal , Pabitra Badhuk
IPC: F23R3/06
Abstract: A combustor comprising a dome wall, a combustor liner extending from the dome wall, and a combustion chamber at least partially defined by the dome wall and the combustor liner. A set of fuel cups are arranged along the dome wall. A set of dilution passages extend through the dome wall or the combustor liner to direct air into the combustion chamber, wherein a dilution passage of the set of dilution passages includes an inlet, an outlet, and a passageway.
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