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公开(公告)号：US12228286B1
公开(公告)日：2025-02-18
申请号：US18477597
申请日：2023-09-29
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Pradeep Naik , Hiranya Kumar Nath , Perumallu Vukanti , Clayton S. Cooper , Steven C. Vise , Michael A. Benjamin , R Narasimha Chiranthan
Abstract: A combustion section of a turbine engine having a primary combustion chamber and a secondary combustion chamber. The primary combustion chamber is defined, at least in part, by a combustor liner and a dome wall. A primary fuel nozzle having an outlet is located at the dome wall, wherein the outlet of the primary fuel nozzle is fluidly coupled with the primary combustion chamber. At least one opening located in an outer liner axially aft of the dome wall fluidly couples the secondary combustion chamber and the primary combustion chamber. A set of secondary fuel nozzles are fluidly coupled with the secondary combustion chamber.
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公开(公告)号：US20240052778A1
公开(公告)日：2024-02-15
申请号：US17951619
申请日：2022-09-23
Applicant: General Electric Company
Inventor： Nageswar Rao Ganji , Ravindra Shankar Ganiger , Hiranya Kumar Nath , Ambika Shivamurthy , Trevor H. Wood
CPC classification number: F02C6/08 , F01D25/04 , F01D25/28 , F05D2260/606 , F05D2260/963 , F05D2250/131
Abstract: Variable bleed valves with struts for aerodynamic stability are described. An apparatus described herein includes a variable bleed valve port, and a strut disposed within the variable bleed valve port, the strut defining a plane and a plurality of holes disposed perpendicularly to the plane, the plurality of holes disposed in a pattern to dampen an acoustic response associated with the variable bleed valve port.
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公开(公告)号：US11846423B2
公开(公告)日：2023-12-19
申请号：US17232691
申请日：2021-04-16
Applicant: General Electric Company
Inventor： Steven Clayton Vise , Clayton Stuart Cooper , Michael Anthony Benjamin , Hiranya Kumar Nath , Rameshkumar Muthuvel Chandrasekaran
IPC: F23R3/28 , F02M61/18 , B01F23/21 , B01F25/10 , B01F23/213 , B01F101/00
CPC classification number: F23R3/286 , B01F23/2132 , B01F25/10 , F02M61/18 , B01F2101/503
Abstract: A mixer assembly having a plurality of mixer vanes, each of the plurality of mixer vanes having a first end, a second end, and a body portion extending between the first end and the second end, the body portion having a length, a width, a thickness, a cross-sectional area, a curvature, and a twist, wherein each of the plurality of mixer vanes has a 3-dimensional shape defined by the length, width, thickness, cross-sectional area, curvature, and twist of the body portion, and wherein at least one of the plurality of mixer vanes has a non-uniform 3-dimensional shape.
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公开(公告)号：US11774098B2
公开(公告)日：2023-10-03
申请号：US17340585
申请日：2021-06-07
Applicant: General Electric Company
Inventor： Pradeep Naik , Rimple Rakeshkumar Rangrej , Saket Singh , Narasimha Chiranthan R , Shai Birmaher , Hiranya Kumar Nath , Ravindra Shankar Ganiger
CPC classification number: F23R3/16 , F23R3/002 , F23R3/06 , F23R3/08 , F23R3/346 , F23M5/085 , F23M2900/05002 , F23R2900/00014 , F23R2900/03042
Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a forward liner segment; an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber; and a fence disposed between the forward and aft liner segments, wherein the fence extends in the circumferential direction, and wherein the fence extends into the combustion chamber along the radial direction.
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公开(公告)号：US11725817B2
公开(公告)日：2023-08-15
申请号：US17363088
申请日：2021-06-30
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Hiranya Kumar Nath , Rajendra Mahadeorao Wankhade , Daniel J. Kirtley , Michael Anthony Benjamin
CPC classification number: F23R3/08 , F01D9/023 , F23R3/002 , F23R3/06 , F23R3/60 , F02C7/28 , F05D2220/32 , F05D2240/35 , F05D2240/55 , F23R3/005
Abstract: A gas turbine engine and combustor assembly are provided, the combustor assembly including a first liner and a second liner together defining at least in part a combustion chamber, wherein the first liner and the second liner are separated by a gap along the longitudinal direction, and wherein the first liner is forward of the second liner relative to a flow of fluid through the combustion chamber along the longitudinal direction, and wherein the gap is extended along the circumferential direction.
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Patent Agency Ranking
公开(公告)号：US20220390110A1
公开(公告)日：2022-12-08
申请号：US17340585
申请日：2021-06-07
Applicant: General Electric Company
Inventor： Pradeep Naik , Rimple Rakeshkumar Rangrej , Saket Singh , Narasimha Chiranthan R , Shai Birmaher , Hiranya Kumar Nath , Ravindra Shankar Ganiger
Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a forward liner segment; an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber; and a fence disposed between the forward and aft liner segments, wherein the fence extends in the circumferential direction, and wherein the fence extends into the combustion chamber along the radial direction.
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公开(公告)号：US20220333782A1
公开(公告)日：2022-10-20
申请号：US17232691
申请日：2021-04-16
Applicant: General Electric Company
Inventor： Steven Clayton Vise , Clayton Stuart Cooper , Michael Anthony Benjamin , Hiranya Kumar Nath , Rameshkumar Muthuvel Chandrasekaran
Abstract: A mixer assembly having a plurality of mixer vanes, each of the plurality of mixer vanes having a first end, a second end, and a body portion extending between the first end and the second end, the body portion having a length, a width, a thickness, a cross-sectional area, a curvature, and a twist, wherein each of the plurality of mixer vanes has a 3-dimensional shape defined by the length, width, thickness, cross-sectional area, curvature, and twist of the body portion, and wherein at least one of the plurality of mixer vanes has a non-uniform 3-dimensional shape.
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公开(公告)号：US20190249874A1
公开(公告)日：2019-08-15
申请号：US15896223
申请日：2018-02-14
Applicant: General Electric Company
Inventor： Gurunath Gandikota , Hiranya Kumar Nath , Arvind Kumar Rao , Steven Clayton Vise , Perumallu Vukanti , Mayank Krisna Amble , Clayton Stuart Cooper
CPC classification number: F23R3/002 , F23R3/08 , F23R3/14 , F23R3/16 , F23R2900/03042
Abstract: A gas turbine engine combustor includes a liner defining at least in part a combustion chamber, a first side exposed to the combustion chamber, a second side opposite the first side, and a dilution hole extending from the second side to the first side. The liner includes an airflow feature on the first side of the liner adjacent to the dilution hole and extending into the combustion chamber to increase a cooling of the liner.
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公开(公告)号：US12146441B1
公开(公告)日：2024-11-19
申请号：US18456391
申请日：2023-08-25
Applicant: General Electric Company
Inventor： Paul Mathew , Ravindra Shankar Ganiger , David Raju Yamarthi , Rachamadugu Sivaprasad , Michael Joseph Murray , Hiranya Kumar Nath
Abstract: Methods and apparatus to maintain a state of a fluid in a system are disclosed. An example system includes a pump including a primary inlet, a primary outlet, and a secondary inlet, at least one injector including a first inlet, a second inlet, and at least one outlet, a third conduit coupled to a first conduit upstream of the primary inlet and coupled to the at least one injector at the first inlet to deliver the fluid, a fourth conduit coupled to a second conduit downstream of the primary outlet and coupled to the at least one injector at the second inlet to deliver the fluid, and a fifth conduit coupled to the at least one injector at the at least one outlet to receive the fluid and coupled to the pump at the secondary inlet.
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公开(公告)号：US20240247807A1
公开(公告)日：2024-07-25
申请号：US18585509
申请日：2024-02-23
Applicant: General Electric Company
Inventor： Karthikeyan Sampath , Pradeep Naik , Veeraraju Vanapalli , Perumallu Vukanti , Shai Birmaher , Daniel J. Kirtley , Deepak Ghiya , Rample Rakeshkumar Rangrej , Saket Singh , Ravindra Shankar Ganiger , Hiranya Kumar Nath , Michael Anthony Benjamin , Rajendra Mahadeorao Wankhade
CPC classification number: F23R3/60 , F23R3/06 , B33Y80/00 , F23R2900/00012 , F23R2900/00017 , F23R2900/00018
Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a forward liner segment; an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber; and an intermediate member disposed at least partially between the forward and aft liner segments and extending in the circumferential direction.
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