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公开(公告)号：US11959643B2
公开(公告)日：2024-04-16
申请号：US17340856
申请日：2021-06-07
Applicant: General Electric Company
Inventor： Karthikeyan Sampath , Pradeep Naik , Veeraraju Vanapalli , Perumallu Vukanti , Shai Birmaher , Daniel J. Kirtley , Deepak Ghiya , Rimple 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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公开(公告)号：US11920796B2
公开(公告)日：2024-03-05
申请号：US17340856
申请日：2021-06-07
Applicant: General Electric Company
Inventor： Karthikeyan Sampath , Pradeep Naik , Veeraraju Vanapalli , Perumallu Vukanti , Shai Birmaher , Daniel J. Kirtley , Deepak Ghiya , Rimple 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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公开(公告)号：US11885495B2
公开(公告)日：2024-01-30
申请号：US17340816
申请日：2021-06-07
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Hiranya Kumar Nath , Daniel J. Kirtley , Shai Birmaher , Pradeep Naik
CPC classification number: F23R3/002 , F02C3/00 , F02C3/14 , F23R3/06 , F05D2220/32 , F05D2240/35 , F23R2900/03043
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 liner at least partially defining a combustion chamber of the gas turbine engine, wherein the liner comprises a looped feature.
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公开(公告)号：US20230323835A1
公开(公告)日：2023-10-12
申请号：US17838603
申请日：2022-06-13
Applicant: General Electric Company
Inventor： Rajesh Kumar , Prateek Jalan , Kudum Shinde , Atanu Saha , Hiranya Kumar Nath , Ravindra Shankar Ganiger
CPC classification number: F02K3/02 , F05D2260/20 , F02C7/12
Abstract: A gas turbine engine includes a casing, a rotor assembly rotatably mounted within the casing, the rotor assembly comprising a forward rotor portion defining a forward rotor cavity and an aft rotor portion defining an aft rotor cavity, the aft rotor cavity being fluidly isolated from the forward rotor cavity, and a cooling system. The cooling system includes a forward cooling fluid supply, a forward supply line providing fluid communication between the forward cooling fluid supply and the forward rotor cavity, an aft cooling fluid supply, an aft supply line providing fluid communication between the aft cooling fluid supply and the aft rotor cavity, and a flow control system fluidly coupled to the forward supply line and the aft supply line for regulating a flow of forward cooling fluid and a flow of aft cooling fluid.
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公开(公告)号：US20230212984A1
公开(公告)日：2023-07-06
申请号：US17692411
申请日：2022-03-11
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Steven C. Vise , Pradeep Naik , Perumallu Vukanti , Michael T. Bucaro , Ajoy Patra , R Narasimha Chiranthan , Michael A. Benjamin , Manampathy G. Giridharan , Hiranya Kumar Nath
CPC classification number: F02C7/232 , F23R3/28 , F05D2220/32 , F05D2240/35
Abstract: An engine can utilize a combustor to combust fuel to drive the engine. A fuel nozzle assembly can supply fuel to the combustor for combustion or ignition of the fuel. The fuel nozzle assembly can include a swirler and a fuel nozzle to supply a mixture of fuel and air for combustion. Varying the geometry of the swirler can provide for improved supply of air, which can improve efficiency and flame control.
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Patent Agency Ranking
公开(公告)号：US11549686B2
公开(公告)日：2023-01-10
申请号：US17751886
申请日：2022-05-24
Applicant: General Electric Company
IPC: F23R3/00
Abstract: A combustor for a gas turbine engine includes a forward liner segment and an aft liner segment positioned downstream from the forward liner segment relative to a direction of flow through the combustor. The forward and aft liner segments at least partially define a combustion chamber. Furthermore, the combustor includes a dilution slot frame positioned between the forward and aft liner segments along a longitudinal centerline of the gas turbine engine. Moreover, the dilution slot frame defines a plurality of dilution slots spaced apart from each other along a circumferential direction of the gas turbine engine such that the plurality of dilution slots provides an annular ring of dilution air to the combustion chamber.
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公开(公告)号：US11371701B1
公开(公告)日：2022-06-28
申请号：US17166687
申请日：2021-02-03
Applicant: General Electric Company
IPC: F23R3/00
Abstract: A combustor for a gas turbine engine includes a forward liner segment and an aft liner segment positioned downstream from the forward liner segment relative to a direction of flow through the combustor. The forward and aft liner segments at least partially define a combustion chamber. Furthermore, the combustor includes a dilution slot frame positioned between the forward and aft liner segments along a longitudinal centerline of the gas turbine engine. Moreover, the dilution slot frame defines a plurality of dilution slots spaced apart from each other along a circumferential direction of the gas turbine engine such that the plurality of dilution slots provides an annular ring of dilution air to the combustion chamber.
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公开(公告)号：US20220195931A1
公开(公告)日：2022-06-23
申请号：US17130040
申请日：2020-12-22
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Hiranya Kumar Nath , Michael Anthony Benjamin , Rajendra Mahadeorao Wankhade , Gurunath Gandikota
Abstract: A combustor for a gas turbine engine includes an inner liner and an outer liner positioned outward of the inner liner along the radial direction such that a combustion chamber is defined between the inner and outer liners. Furthermore, the combustor includes a fuel nozzle configured to supply fuel to the combustion chamber. Moreover, the combustor includes a bristle pack having a base plate and a plurality of bristles extending outward from the base plate such that the bristle pack forms at least a portion of at least one of a heat shield coupled to the fuel nozzle, a deflector of the combustor, or a flare of the combustor.
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公开(公告)号：US20250109853A1
公开(公告)日：2025-04-03
申请号：US18476595
申请日：2023-09-28
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Pradeep Naik , Perumallu Vukanti , Ravindra Shankar Ganiger , Sahana Narasimhan Suresh , Clayton S. Cooper , Michael A. Benjamin , Steven C. Vise , Sripathi Mohan , Hiranya Kumar Nath
Abstract: A turbine engine with a compressor section, a combustion section, and a turbine section in serial flow arrangement along an engine centerline. The combustion section includes a primary combustor liner including an inner liner and an outer liner. A dome wall and a primary dome inlet are located in the dome wall. The outer liner defines at least one opening downstream from the primary dome inlet. A primary combustion chamber and a set of secondary combustors are fluidly coupled to the primary combustion chamber at the at least one opening.
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公开(公告)号：US12180897B2
公开(公告)日：2024-12-31
申请号：US18353741
申请日：2023-07-17
Applicant: General Electric Company
Inventor： Thomas Malkus , Trevor H. Wood , Giridhar Jothiprasad , Nageswar Ganji , Hiranya Kumar Nath , Ravindra Shankar Ganiger , Ambika Shivamurthy
Abstract: Aero-acoustically damped bleed valves are disclosed. An example variable bleed valve apparatus comprises a variable bleed valve door to actuate the variable bleed valve apparatus, and a variable bleed valve port including an upstream edge and a downstream edge, the VBV port to define a secondary flowpath, the VBV door to cover the VBV port in a closed position, and a vortex device at the upstream edge of the variable bleed valve port, the vortex device including a vorticity generating feature along the upstream edge of the variable bleed valve port.
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