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公开(公告)号：US20230042970A1
公开(公告)日：2023-02-09
申请号：US17394848
申请日：2021-08-05
Applicant: General Electric Company
Inventor： Gurunath Gandikota , Karthikeyan Sampath , Perumallu Vukanti , Allen M. Danis , Scott M. Bush , Steven Clayton Vise , Hari Ravi Chandra , Rimple Rangrej , Saket Singh , Pradeep Naik , Neeraj Kumar Mishra , Arvind Kumar Rao , Balasubramaniam Venkatanarayanan , Ranjeet Kumar Mishra
IPC: F23R3/14
Abstract: A dome assembly for a combustor includes: at least one swirler assembly including: at least one swirler including a plurality of swirl vanes arrayed about an axis, the plurality of swirl vanes oriented so as to impart a tangential velocity to air passing through the swirler parallel to the axis; each of the plurality of swirl vanes having a thickness and including a plurality of edges which collectively define a peripheral boundary of the respective swirl vane; wherein at least a selected one of the plurality of swirl vanes includes at least one void passing through the thickness of the selected swirl vane, the void disposed within the peripheral boundary of the selected swirl vane.
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公开(公告)号：US20230033628A1
公开(公告)日：2023-02-02
申请号：US17389030
申请日：2021-07-29
Applicant: General Electric Company
Inventor： Rimple Rangrej , Saket Singh , Pradeep Naik
Abstract: A main mixer for an engine. The main mixer includes a plurality of mixer vanes located circumferentially around a mixer body. Each mixer vane includes a waveform profile. The waveform profile detaches or trips a boundary layer of an air flow across the mixer vane such that the waveform profile introduces turbulence into the air flow.
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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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公开(公告)号：US12152778B1
公开(公告)日：2024-11-26
申请号：US18345342
申请日：2023-06-30
Applicant: General Electric Company
Inventor： Ranganatha Narasimha Chiranthan , Rimple Rangrej , Saket Singh , Pradeep Naik
Abstract: A liner for a combustor in a gas turbine engine. The liner includes a liner body having a cold side and a hot side, a dilution opening extending through the liner body, a first passage positioned adjacent the dilution opening and extending through the liner body from the cold side to the hot side, and a second passage positioned adjacent the dilution opening and extending through the liner body from the cold side to the hot side, the second passage being separate from the first passage and being located on a diametrically opposing side of the dilution opening from the first passage. A dilution flow flows through the dilution opening from the cold side to the hot side and a secondary flow flows through the first passage and the second passage from the cold side to the hot side.
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公开(公告)号：US12123596B2
公开(公告)日：2024-10-22
申请号：US17389022
申请日：2021-07-29
Applicant: General Electric Company
Inventor： Rimple Rangrej , Saket Singh , Pradeep Naik , Neeraj Mishra
IPC: F23R3/14
CPC classification number: F23R3/14 , F05D2240/127 , F05D2240/35 , F05D2250/183
Abstract: A gas turbine combustor includes a main mixer for providing an air flow to mix with a fuel flow in a combustor. The main mixer includes an annular mixer body, a plurality of mixer vanes located circumferentially around the annular mixer body, and a plurality of wedges extending radially outward from each of the plurality of mixer vanes. At least one of the wedges includes serrations. The air flow through the main mixer enters the main mixer at a leading edge of the mixer vane, flows over the plurality of wedges, and exits the mixer vanes at a trailing edge of the main mixer. The wedges create vortices in the air flow to provide a uniform fuel-air flow.
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Patent Agency Ranking
公开(公告)号：US20240133552A1
公开(公告)日：2024-04-25
申请号：US18314418
申请日：2023-05-08
Applicant: General Electric Company
Inventor： Karthikeyan Sampath , Rimple Rangrej , Pradeep Naik , Saket Singh , Deepak Ghiya , Perumallu Vukanti
CPC classification number: F23R3/002 , F23R3/60 , F23R2900/00014
Abstract: In one aspect, a combustor for a turbomachine engine includes a combustion chamber and a component in operable flow with the combustion chamber. The component has a porous structure that defines multiple channels, that are adapted to configure the component as a damper to reduce combustion dynamics of the combustor. In another aspect, a combustor of a turbomachine engine includes a diffuser, a combustor component positioned aft of the diffuser to receive cooling air therefrom, and a support structure in operable flow with the diffuser and the combustor component and positioned therebetween. The support structure has a porous structure that defines multiple channels, which are adapted to improve a backflow margin of the cooling air by reducing turbulence of the cooling air.
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公开(公告)号：US20240102653A1
公开(公告)日：2024-03-28
申请号：US18529428
申请日：2023-12-05
Applicant: General Electric Company
Inventor： Saket Singh , Ravindra Shankar Ganiger , Hiranya Nath , Perumallu Vukanti , Ajoy Patra , Karthikeyan Sampath , Pradeep Naik , Rimple Rangrej , Veera Venkata Amarnath Manem
CPC classification number: F23R3/002 , F23R3/60 , F23R2900/00017 , F23R2900/03043
Abstract: A dome-deflector assembly for a gas turbine includes a dome, a deflector, and at least one dome-deflector connecting assembly that includes a connecting member connecting the dome and the deflector together with a cavity being defined between the dome and the deflector. The connecting member extends through the deflector and has a first end arranged at a hot surface side of the deflector and a second end arranged to connect with the dome. The dome-deflector connecting assembly is configured to provide a flow of cooling air from the cavity to the hot surface side of the deflector to cool the first end of the connecting member on the hot surface side of the deflector.
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公开(公告)号：US11846419B2
公开(公告)日：2023-12-19
申请号：US17810678
申请日：2022-07-05
Applicant: General Electric Company
Inventor： Saket Singh , Ravindra Shankar Ganiger , Hiranya Nath , Perumallu Vukanti , Ajoy Patra , Karthikeyan Sampath , Pradeep Naik , Rimple Rangrej , Veera Venkata Amarnath Manem
CPC classification number: F23R3/002 , F23R3/60 , F23R2900/00017 , F23R2900/03043
Abstract: A dome-deflector assembly for a gas turbine includes a dome, a deflector, and at least one dome-deflector connecting assembly that includes a connecting member connecting the dome and the deflector together with a cavity being defined between the dome and the deflector. The connecting member extends through the deflector and has a first end arranged at a hot surface side of the deflector and a second end arranged to connect with the dome. The dome-deflector connecting assembly is configured to provide a flow of cooling air from the cavity to the hot surface side of the deflector to cool the first end of the connecting member on the hot surface side of the deflector.
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公开(公告)号：US11815267B2
公开(公告)日：2023-11-14
申请号：US17809381
申请日：2022-06-28
Applicant: General Electric Company
Inventor： Ranganatha Narasimha Chiranthan , Karthikeyan Sampath , Perumallu Vukanti , Rimple Rangrej , Ravindra Shankar Ganiger , Hiranya Nath
CPC classification number: F23R3/16 , F23R3/06 , F23R2900/00001 , F23R2900/03044 , F23R2900/03045
Abstract: A combustor liner for a gas turbine has a cold side liner segment, and a hot side liner segment, with a baffle cavity between the cold side liner segment and the hot side liner segment. At least one cooling airflow dispersing member is arranged within the baffle cavity. The at least one cooling airflow dispersing member includes a main cavity portion, and at least one peripheral cavity portion surrounding the main cavity portion. The main cavity portion includes a main cavity inlet side having a cooling airflow opening, a main cavity outlet side having plurality of hot side cooling airflow openings, and at least one peripheral cavity outlet flow passage providing fluid communication between the main cavity portion and the at least one peripheral cavity portion. The at least one peripheral cavity portion includes a peripheral cavity outlet side having a plurality of hot side cooling airflow openings.
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公开(公告)号：US20230288065A1
公开(公告)日：2023-09-14
申请号：US17810678
申请日：2022-07-05
Applicant: General Electric Company
Inventor： Saket Singh , Ravindra Shankar Ganiger , Hiranya Nath , Perumallu Vukanti , Ajoy Patra , Karthikeyan Sampath , Pradeep Naik , Rimple Rangrej , Veera Venkata Amarnath Manem
CPC classification number: F23R3/002 , F23R3/60 , F23R2900/00017 , F23R2900/03043
Abstract: A dome-deflector assembly for a gas turbine includes a dome, a deflector, and at least one dome-deflector connecting assembly that includes a connecting member connecting the dome and the deflector together with a cavity being defined between the dome and the deflector. The connecting member extends through the deflector and has a first end arranged at a hot surface side of the deflector and a second end arranged to connect with the dome. The dome-deflector connecting assembly is configured to provide a flow of cooling air from the cavity to the hot surface side of the deflector to cool the first end of the connecting member on the hot surface side of the deflector.
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