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公开(公告)号：US10465907B2
公开(公告)日：2019-11-05
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
IPC: F23R3/04 , F23R3/00 , F23R3/10 , F23R3/28 , F23R3/44 , F23R3/46 , F04D29/54 , F23R3/50 , F23R3/54
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.
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公开(公告)号：US10352569B2
公开(公告)日：2019-07-16
申请号：US15343672
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
Abstract: The present disclosure is directed to a fuel injector for a gas turbine engine. The fuel injector includes an end wall defining a fluid chamber, a centerbody, an outer sleeve surrounding the centerbody from the end wall toward a downstream end of the fuel injector, and a fluid cavity wall. The centerbody includes an axially extended outer wall and inner wall extended from the end wall toward the 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 fluid conduit is in fluid communication with the fluid chamber. The outer wall defines at least one radially oriented fluid injection port in fluid communication with the fluid conduit. 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 further defines a plurality of radially oriented first air inlet ports in circumferential arrangement at a first axial portion of the outer sleeve, and a plurality of radially oriented second air inlet ports in circumferential arrangement at a second axial portion of the outer sleeve. The fluid cavity wall is disposed axially between the first air inlet port and the second air inlet port and extends radially from the outer sleeve toward the centerbody. The fluid cavity wall defines a fluid cavity and a second fluid injection port in fluid communication with the fluid cavity. The second fluid injection port is in fluid communication with the premix passage.
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公开(公告)号：US10337738B2
公开(公告)日：2019-07-02
申请号：US15189085
申请日：2016-06-22
Applicant: General Electric Company
Inventor： Gregory Allen Boardman , Pradeep Naik , Allen Michael Danis
Abstract: A rich-quench-lean combustor assembly for a gas turbine engine includes a fuel nozzle and a dome, the fuel nozzle attached to the dome. The combustor assembly additionally includes a liner attached to or formed integrally with the dome, the liner and the dome together defining at least in part a combustion chamber. Additionally, the liner extends between a forward end and an aft end. The liner includes a plurality of quench air jets positioned between the forward end and aft end and defines a forward section extending from the quench air jets to the dome. The dome and the forward section of the liner are configured to be cooled substantially by one or both of impingement cooling or convective cooling.
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公开(公告)号：US10295190B2
公开(公告)日：2019-05-21
申请号：US15343601
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
Abstract: The present disclosure is directed to a fuel injector for a gas turbine engine including an end wall defining a fluid chamber, a centerbody, and an outer sleeve surrounding the centerbody from the end wall toward a downstream end of the fuel injector. The centerbody includes an axially extended outer wall and inner wall. The outer wall and inner wall extend from the end wall toward the 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 fluid conduit is in fluid communication with the fluid chamber. The outer wall defines at least one radially oriented fluid injection port in fluid communication with the fluid conduit. 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.
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Patent Agency Ranking
公开(公告)号：US20190086085A1
公开(公告)日：2019-03-21
申请号：US15711203
申请日：2017-09-21
Applicant: General Electric Company
Inventor： David Albin Lind , Rishikesh Karande , Pradeep Naik , Ajoy Patra , Gregory Allen Boardman
CPC classification number: F23R3/04 , F02C7/12 , F02C7/24 , F05D2220/32 , F05D2240/128 , F05D2240/35 , F05D2260/99 , F23R3/002 , F23R3/02 , F23R3/28 , F23R3/50 , F23R2900/00014
Abstract: The present disclosure is directed to a combustion section for a gas turbine engine. The combustion section includes a combustor assembly, an outer casing, a fuel injector assembly, and an inner casing. The combustor assembly includes an inner liner and an outer liner each extended at least partially along a lengthwise direction and at an acute angle relative to the longitudinal centerline. The combustor assembly further includes a dome assembly extended between the inner liner and the outer liner. The dome assembly, the inner liner, and the outer liner together define a combustion chamber therebetween. The combustor assembly still further includes a bulkhead assembly defining a plurality of walls coupled to the inner liner and generally surrounding the outer liner and dome assembly. At least a portion of the bulkhead assembly is extended at least partially along a forward direction and defines a plenum between the bulkhead assembly and the dome assembly. The outer casing surrounds the combustor assembly and is extended at least partially co-directional to the combustor assembly. The fuel injector assembly is extended through the outer casing, the bulkhead assembly, and the dome assembly. The inner casing, the outer casing, and the combustor assembly together define a primary flowpath in direct fluid communication with the combustion chamber. The primary flowpath is extended at least along a forward direction and an aft direction defined by inner casing, the outer casing, and the combustor assembly. An oxidizer flows through the primary flowpath in serial flow through the plenum and the fuel injector assembly into the combustion chamber.
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公开(公告)号：US20190085767A1
公开(公告)日：2019-03-21
申请号：US15705314
申请日：2017-09-15
Applicant: General Electric Company
Inventor： Steven Clayton Vise , Allen Michael Danis , Jayanth Sekar , Pradeep Naik , Perumallu Vukanti , Arthur Wesley Johnson , Clayton Stuart Cooper , Karthikeyan Sampath
Abstract: An apparatus and method for a combustor, the combustor including combustor liner having a plurality of dilution openings. The combustor receives a flow of fuel that is ignited and mixed with dilution air to form a flow of combustion gases. The flow of combustion gases travels through the combustor to a turbine section of an engine.
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公开(公告)号：US10197279B2
公开(公告)日：2019-02-05
申请号：US15189074
申请日：2016-06-22
Applicant: General Electric Company
Inventor： Gregory Allen Boardman , Pradeep Naik , Allen Michael Danis
Abstract: A rich-quench-lean combustor assembly for a gas turbine engine includes a fuel nozzle and a dome, the fuel nozzle attached to the dome. The combustor assembly additionally includes a liner attached to or formed integrally with the dome, the liner and the dome together defining at least in part a combustion chamber. The liner extends between a forward end and an aft end. The liner includes a plurality of quench air jets positioned between the forward end and aft end. The quench air jets include a plurality of primary stage air jets and a plurality of secondary stage air jets. The plurality of primary stage air jets are each spaced from the plurality of secondary stage air jets along the axial direction and together provide the combustion chamber with a quench airflow.
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公开(公告)号：US20170370588A1
公开(公告)日：2017-12-28
申请号：US15189061
申请日：2016-06-22
Applicant: General Electric Company
Inventor： Gregory Allen Boardman , Pradeep Naik , Allen Michael Danis
CPC classification number: F23R3/286 , F02C3/04 , F02C7/12 , F02C7/222 , F05D2220/32 , F05D2260/201 , F23R3/002 , F23R3/06 , F23R3/283 , F23R2900/03043 , F23R2900/03044 , Y02T50/675
Abstract: A rich-quench-lean combustor assembly for a gas turbine engine includes a liner extending between a forward end and an aft end. The liner includes a plurality of quench air jets positioned between the forward end and the aft end. The combustor assembly additionally includes a dome attached to or formed integrally with the liner, the dome and the liner together defining at least in part a combustion chamber. A fuel nozzle is attached to the dome, the fuel nozzle configured as a premix fuel nozzle for providing a substantially homogenous mixture of fuel and air to the combustion chamber, the mixture of fuel and air having an equivalence ratio of at least 1.5.
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公开(公告)号：US20170370584A1
公开(公告)日：2017-12-28
申请号：US15189074
申请日：2016-06-22
Applicant: General Electric Company
Inventor： Gregory Allen Boardman , Pradeep Naik , Allen Michael Danis
CPC classification number: F23R3/06 , F01D25/24 , F02C3/04 , F05D2220/32 , F23D11/383 , F23R3/002 , F23R3/007 , F23R3/14 , F23R3/286 , F23R2900/03043 , F23R2900/03044 , Y02T50/675
Abstract: A rich-quench-lean combustor assembly for a gas turbine engine includes a fuel nozzle and a dome, the fuel nozzle attached to the dome. The combustor assembly additionally includes a liner attached to or formed integrally with the dome, the liner and the dome together defining at least in part a combustion chamber. The liner extends between a forward end and an aft end. The liner includes a plurality of quench air jets positioned between the forward end and aft end. The quench air jets include a plurality of primary stage air jets and a plurality of secondary stage air jets. The plurality of primary stage air jets are each spaced from the plurality of secondary stage air jets along the axial direction and together provide the combustion chamber with a quench airflow.
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