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公开(公告)号：US11022313B2
公开(公告)日：2021-06-01
申请号：US15189061
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 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：US20200248903A1
公开(公告)日：2020-08-06
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：US10598380B2
公开(公告)日：2020-03-24
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
Abstract: The present disclosure is directed to a combustion section for a gas turbine engine including a combustor assembly, an outer casing, a fuel injector assembly, and an inner casing. An inner liner and an outer liner are each extended at least partially along a lengthwise direction and at an acute angle. A dome assembly is extended between the inner liner and the outer liner, and the inner liner, and the outer liner together define a combustion chamber therebetween. A bulkhead assembly defining a plurality of walls is coupled to the inner liner and generally surrounding the outer liner and dome assembly. The outer casing surrounds the combustor assembly. The inner casing, the outer casing, and the combustor assembly together define a primary flowpath. 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：US20190271470A1
公开(公告)日：2019-09-05
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：US20190212009A1
公开(公告)日：2019-07-11
申请号：US15865809
申请日：2018-01-09
Applicant: General Electric Company
Inventor： Gregory Allen Boardman , Jeffrey Michael Martini , Michael Anthony Benjamin , Pradeep Naik
Abstract: A fuel injector for a gas turbine engine including an outer sleeve. An upstream end of the outer sleeve defines an inlet opening and a downstream end defines an exit opening, each of which defined within the outer sleeve. The outer sleeve defines a radial opening extended therethrough along the radial direction. At least a portion of the outer sleeve defines a plurality of grooves. The outer sleeve defines a fuel conduit through at least a portion of the outer sleeve outward of the plurality of grooves along the radial direction from the fuel injector centerline. The fuel conduit defines a fuel injection opening inward along the radial direction of the radial opening defined through the outer sleeve. A first member of an arm is coupled to the outer sleeve. A second member of the arm is contoured defining a fuel injection port generally concentric to the fuel injector centerline.
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Patent Agency Ranking
公开(公告)号：US20170350598A1
公开(公告)日：2017-12-07
申请号：US15172590
申请日：2016-06-03
Applicant: General Electric Company
Inventor： Gregory Allen Boardman , Pradeep Naik , Joseph Zelina
CPC classification number: F23R3/286 , F02C7/222 , F23R3/14 , F23R3/16 , Y02T50/675
Abstract: The present disclosure is directed to a fuel injector assembly of a gas turbine engine, including a centerbody, an outer sleeve surrounding the centerbody, an inner sleeve disposed between the centerbody and at least a section of the outer sleeve, and at least one axially oriented vane defined between the centerbody and a section of the inner sleeve. A section of the outer sleeve includes at least one radially oriented vane. A portion of the inner sleeve includes a contoured shroud and defines at least one fuel injection port disposed upstream of the contoured shroud. The axially oriented vane is disposed upstream of the fuel injection port.
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公开(公告)号：US20170067639A1
公开(公告)日：2017-03-09
申请号：US14849564
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: F02C3/14 , F02C7/22 , F05D2260/30 , F23R3/04 , F23R3/283 , F23R3/50 , Y02T50/675
Abstract: A system includes an annular combustor having a housing disposed about a head end chamber upstream of a combustion chamber. The annular combustor is configured to extend circumferentially about a rotational axis of a gas turbine engine, and an axis of the combustion chamber is acutely angled relative to the rotational axis. The system also includes a holder coupled to the housing and extending through the head end chamber in an axial direction relative to the axis of the combustion chamber. The holder includes a first receptacle configured to hold a first fuel nozzle, and the holder comprises a first fuel passage extending to the first receptacle.
Abstract translation: 系统包括环形燃烧器，其具有围绕燃烧室上游的头端室设置的壳体。 环形燃烧器被构造成围绕燃气涡轮发动机的旋转轴线周向延伸，并且燃烧室的轴线相对于旋转轴线成锐角。 该系统还包括联接到壳体并且相对于燃烧室的轴线在轴向方向上延伸穿过头端室的保持器。 保持器包括构造成保持第一燃料喷嘴的第一容器，并且保持器包括延伸到第一容器的第一燃料通道。
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公开(公告)号：US20250129940A1
公开(公告)日：2025-04-24
申请号：US18990975
申请日：2024-12-20
Applicant: General Electric Company
Inventor： Pradeep Naik , Shai Birmaher , Saket Singh , Krishnendu Chakraborty
Abstract: A liner for a combustor in a gas turbine engine and a related method. The liner includes a liner body having a cold side and a hot side. The liner includes a dilution passage having a concatenated geometry extending through the liner body. The dilution passage is configured (i) to integrate a first dilution air flow flowing through the dilution passage from the cold side to the hot side and a second dilution air flow flowing through the dilution passage from the cold side to the hot side into an integrated dilution air flow, and (ii) to inject the integrated dilution air flow into a core primary combustion zone of the combustor to attain a predetermined combustion state of the combustor.
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公开(公告)号：US20250075911A1
公开(公告)日：2025-03-06
申请号：US18949096
申请日：2024-11-15
Applicant: General Electric Company
Inventor： Pradeep Naik , Clayton S. Cooper , Perumallu Vukanti , Michael A. Benjamin , Steven C. Vise , Sripathi Mohan
Abstract: A combustor having a main chamber and a trapped vortex cavity. The main chamber includes an outer liner and an inner liner. The trapped vortex cavity extends from at least one of the outer liner or the inner liner. A plurality of mixing assemblies operably injects a fuel-air mixture into the trapped vortex cavity to produce combustion gases. The trapped vortex cavity injects the combustion gases into the main chamber. A steam system is in fluid communication with the main chamber. The steam system operably injecting steam into the main chamber such that the steam flows downstream of the trapped vortex cavity.
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公开(公告)号：US20250075910A1
公开(公告)日：2025-03-06
申请号：US18952330
申请日：2024-11-19
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Pradeep Naik , Joseph Zelina , Sripathi Mohan , Perumallu Vukanti , Clayton S. Cooper , Michael A. Benjamin , Steven C. Vise , Karthikeyan Sampath
Abstract: A turbine engine with a compressor section, a combustion section, and a turbine section in serial flow arrangement along an engine centerline. A combustion section for the turbine engine, having a primary combustor liner including an inner liner and an outer liner annular about an engine centerline. A dome wall extending between the inner liner and the outer liner. A set of primary dome inlets located in the dome wall and circumferentially arranged about the engine centerline. A set of secondary combustors fluidly coupled to a primary combustion chamber, the set of secondary combustors including a first mini combustor and a second mini combustor.
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