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公开(公告)号：US10890329B2
公开(公告)日：2021-01-12
申请号：US15909211
申请日：2018-03-01
Applicant: General Electric Company
Inventor： Gregory Allen Boardman , Pradeep Naik , Jacob Foster , Kediya Vishal Sanjay
Abstract: The present disclosure is directed to a fuel injector including a centerbody defining an air inlet opening defined substantially radially through the centerbody; an outer sleeve surrounding the centerbody, and an end wall coupled to the centerbody and the outer sleeve. The outer sleeve defines a radially oriented first air inlet port defined radially outward of the air inlet opening at the centerbody. A mixing passage is defined between the outer sleeve and the centerbody. A first fuel injection port is defined substantially axially through the end wall to the mixing passage. The first fuel injection port defines a first fuel injection opening at the mixing passage between the first air inlet port at the outer sleeve and the air inlet opening at the centerbody.
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公开(公告)号：US10724740B2
公开(公告)日：2020-07-28
申请号：US15343746
申请日：2016-11-04
Applicant: General Electric Company
Inventor： Gregory Allen Boardman , Marco Venturato , Douglas Downey Turner , Valeria Proano Cadena , William Thomas Bennett
Abstract: The present disclosure is directed to a fuel nozzle for a gas turbine engine, the fuel nozzle defining a radial direction, a longitudinal direction, a circumferential direction, an upstream end, and a downstream end. The fuel nozzle includes an aft body coupled to at least one fuel injector. The aft body defines a forward wall and an aft wall each extended in the radial direction, and a plurality of sidewalls extended in the longitudinal direction. The plurality of sidewalls couples the forward wall and the aft wall. At least one sidewall defines an impingement fluid outlet, and the aft body defines an impingement fluid cavity in fluid communication with the impingement fluid outlet.
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公开(公告)号：US20200173662A1
公开(公告)日：2020-06-04
申请号：US16203997
申请日：2018-11-29
Applicant: General Electric Company
Inventor： Randall Charles Boehm , Gregory Allen Boardman , Ajoy Patra , David Albin Lind , Pradeep Naik , Ranjeet Kumar Mishra
Abstract: A fuel injector assembly for a gas turbine engine is generally provided. The first fuel injector includes a first centerbody surrounding a first walled fuel injection circuit. A first fuel injection port is extended at least partially radially through the first centerbody in fluid communication with the first walled fuel injection circuit. The first centerbody defines a cooling circuit surrounding the first walled fuel injection circuit. The first centerbody defines a plurality of cooling openings at a downstream end of the first centerbody. The plurality of cooling openings is in fluid communication with the cooling circuit. The first centerbody defines an axially extended cooling outlet at the downstream end of the first centerbody.
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公开(公告)号：US20200158342A1
公开(公告)日：2020-05-21
申请号：US16191850
申请日：2018-11-15
Applicant: General Electric Company
Inventor： Gregory Allen Boardman , Pradeep Naik
Abstract: A gas turbine engine including a trapped vortex combustor assembly is generally provided. The combustor assembly includes an inner liner wall extended annularly around a combustor centerline, and an outer liner wall extended annularly around the combustor centerline. The inner liner wall and the outer liner wall together define an involute wall extended at least partially as a spiral curve from a circumferential reference line around the combustor centerline. The involute wall defines an involute combustion chamber. One or more of the inner liner wall and the outer liner wall each define a first dilution opening and a shaped dilution opening.
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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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Patent Agency Ranking
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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公开(公告)号：US20190093895A1
公开(公告)日：2019-03-28
申请号：US15718077
申请日：2017-09-28
Applicant: General Electric Company
Inventor： David Albin Lind , Gregory Allen Boardman
CPC classification number: F23R3/286 , F23D2900/00014 , F23D2900/00015 , F23R3/045 , F23R3/343 , F23R2900/00005 , F23R2900/00014
Abstract: The present disclosure is directed to a fuel injector assembly and a gas turbine engine including the fuel injector assembly. The fuel injector assembly includes a centerbody extended along a lengthwise direction. The centerbody defines a first fuel nozzle. An annular shroud defining a second fuel nozzle surrounds the centerbody and is extended along the lengthwise direction. A passage is defined through the annular shroud and extended generally along the lengthwise direction. The passage defines an exit opening disposed at a downstream end adjacent to the combustion chamber and in fluid communication therewith. The annular shroud defines a fuel inlet opening disposed at an upstream end of the passage. The annular shroud further defines an air inlet opening in fluid communication with the passage. The air inlet opening is disposed between the fuel inlet opening and the exit opening.
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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：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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