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公开(公告)号：US11506388B1
公开(公告)日：2022-11-22
申请号：US17315016
申请日：2021-05-07
Applicant: General Electric Company
Inventor： Gregory A. Boardman , Pradeep Naik , Bassam Sabry Mohammad Abdelnabi , Manampathy G. Giridharan , Vishal Sanjay Kediya , Narasimhan S. Sahana
Abstract: A pilot pre-mixer for a gas turbine engine has a pilot body that includes an internal mixing chamber, a first end on an upstream side of the internal mixing chamber, a second end on a downstream side of the internal mixing chamber, a fuel injector at the first end and communicable with the internal mixing chamber, a plurality of first oxidizer inlet ports arranged to provide an oxidizer agent from outside of the pilot body to the internal mixing chamber, and a plurality of pilot outlet ports at the second end and communicable with the internal mixing chamber, each of the plurality of pilot outlet ports having an outlet on the second end for dispensing a pilot fluid mixture into a combustion zone of a combustor.
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公开(公告)号：US20220364729A1
公开(公告)日：2022-11-17
申请号：US17320756
申请日：2021-05-14
Applicant: General Electric Company
Inventor： Saket Singh , Pradeep Naik , Daniel J. Kirtley , Rimple Rangrej , Ranganatha Narasimha Chiranthan
Abstract: A combustor for a gas turbine engine. The combustor has a combustor liner that includes a vortex turbulence generator. The vortex turbulence generator has a flow passage extending therethrough, the flow passage being defined by a wall about a periphery of the flow passage, and a plurality of vortex generating turbulators disposed on the wall, each of the plurality of vortex generating turbulators a projection portion extending from a surface of the wall into the flow passage and generating a vortex turbulent flow of an oxidizer passing through the flow passage from a cold surface side of the combustor liner to a hot surface side of the combustor liner.
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113.发明申请公开(公告)号：US20220290863A1
公开(公告)日：2022-09-15
申请号：US17199257
申请日：2021-03-11
Applicant: General Electric Company
Inventor： Pradeep Naik , Manampathy G. Giridharan , Vishal Sanjay Kediya , Gregory A. Boardman
Abstract: A mixer for blending fuel and air in a combustor of a turbine engine. The mixer includes a central body having a central passageway and a central axis. The mixer includes a plurality of tubes positioned radially around the central axis and circumferentially around a periphery of the mixer. Each of the tubes of the mixer includes opposed openings and a tangential opening. Each of the tubes of the mixer includes a cylindrical interior mixing passage configured to receive air flow from the opposed openings and the tangential opening and a fuel flow. The opposed openings are configured to spread the fuel flow laterally and the tangential opening is configured to spread the fuel flow tangentially.
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公开(公告)号：US20210207808A1
公开(公告)日：2021-07-08
申请号：US16737040
申请日：2020-01-08
Applicant: General Electric Company
Inventor： Ranjeet Kumar Mishra , Jayanth Sekar , Pradeep Naik , Gregory A. Boardman , Randall C. Boehm
IPC: F23R3/16
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：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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Patent Agency Ranking
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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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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