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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：US11913376B2
公开(公告)日：2024-02-27
申请号：US17663308
申请日：2022-05-13
Applicant: General Electric Company
Inventor： Kudum Shinde , Ravindra Shankar Ganiger
CPC classification number: F02C3/04 , F01D5/06 , F01D21/00 , F01D25/34 , F02C7/18 , F02C7/32 , F02C7/36 , F04D29/321 , F05D2220/323 , F05D2240/35 , F05D2240/60
Abstract: A gas turbine engine includes a compressor section with a compressor rotor shaft assembly including a plurality of compressor rotors longitudinally spaced apart from each other via respective ones of a plurality of shaft sections of a rotor shaft, each compressor rotor of the plurality of compressor rotors having a plurality of rotor vanes extending radially outward therefrom and being circumferentially spaced about the compressor rotor. A stator shroud assembly has a stator shroud casing surrounding the compressor rotor shaft assembly, a compressor flow passage being defined between the compressor rotor shaft assembly and the stator shroud casing. A pressurized air source generates a flow of pressurized air to be provided to the compressor section, and a plurality of pressurized airflow nozzles are connected with the pressurized air source and provide the flow of pressurized air into the compressor flow passage to cause the compressor rotor shaft assembly to rotate.
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公开(公告)号：US20240053009A1
公开(公告)日：2024-02-15
申请号：US18066427
申请日：2022-12-15
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Hiranya Nath , Deepti Bhandari , Girish Kamath Cannanore
CPC classification number: F23R3/002 , F23R3/16 , F02C7/00 , F05D2220/32 , F05D2240/35
Abstract: A combustor for a gas turbine includes a dome structure including a dome-side swirler opening therethrough, and a deflector connected to the dome structure. The deflector includes a deflector-side swirler opening therethrough and a deflector-dome connecting member arranged at the deflector-side swirler opening. The deflector-dome connecting member is connected with the dome-side swirler opening via a snap-fit type connection.
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公开(公告)号：US11898755B2
公开(公告)日：2024-02-13
申请号：US17805983
申请日：2022-06-08
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Hiranya Nath , Michael A. Benjamin , Nicholas R. Overman
CPC classification number: F23R3/346 , F23R3/002 , F23R3/26 , F23R2900/00014 , F23R2900/03044
Abstract: A combustor for a gas turbine has a combustor liner including an outer liner and an inner liner, a combustion chamber being defined between the outer liner and the inner liner. The combustion chamber includes a primary combustion zone at an upstream end of the combustion chamber. The combustor also includes an outer liner expanded primary volume portion, and a secondary outer liner portion. One of the outer liner expanded primary volume portion and the secondary outer liner portion is movable to adjust a volume of the primary combustion zone by opening and closing access to the outer liner expanded primary volume portion so as to increase and to decrease the volume of the primary combustion zone.
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公开(公告)号：US11891905B2
公开(公告)日：2024-02-06
申请号：US17644475
申请日：2021-12-15
Applicant: General Electric Company
Inventor： Prashant Bhujabal , Ravindra Shankar Ganiger , Narayanan Payyoor , Mohankumar Banakar , Weize Kang
CPC classification number: F01D25/162 , F01D5/06 , F02C7/06 , F05D2240/54 , F05D2240/61 , F05D2260/40311
Abstract: A bearing support assembly to support one or more bearings on a shaft. The bearing support assembly includes a bearing support frame configured to be coupled to a static frame, a plurality of ribs connected to the bearing support frame, and a bearing support connected to the plurality of ribs and configured to support a bearing of the one or more bearings. The bearing support assembly has a non-axisymmetric stiffness around a circumference of the bearing support assembly.
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Patent Agency Ranking
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：US20240001323A1
公开(公告)日：2024-01-04
申请号：US18054735
申请日：2022-11-11
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Hiranya Nath , Thomas D. Woodrow , Scott Alan Schimmels , Arvind Namadevan , Mohan Raju , Subramani Adhiachari , Prasant Bilaiya , Rajesh Kumar
CPC classification number: B01J19/0026 , F16N39/00 , F16N2210/02
Abstract: A self-cleaning conduit for a hydrocarbon fluid. The conduit includes a tube and a mesh. The tube has an interior surface defining a flow passage for the hydrocarbon fluid. The mesh is positioned within the flow passage to abut the interior surface and movable along the interior surface to break-up deposits on the interior surface. The mesh is characterized by a mesh activation parameter (MAP) from one ten thousandths to six tenths.
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公开(公告)号：US11859824B2
公开(公告)日：2024-01-02
申请号：US17931697
申请日：2022-09-13
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Hiranya Nath
CPC classification number: F23R3/60 , F23R3/002 , F23R3/06 , F23R2900/00017 , F23R2900/03044
Abstract: A combustor including a skeleton structure. The combustor further includes at least one liner operably coupled to the skeleton structure to at least partially define a combustion chamber, and a plurality of first planks mounted to a first side of the at least one liner and a plurality of second planks mounted to a second side of the at least one liner. The combustor also includes at least one dilution hole structure provided with a portion of the skeleton structure, and including at least one dilution hole configured to allow fluid to pass therethrough into the combustion chamber.
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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：US11821371B1
公开(公告)日：2023-11-21
申请号：US17816018
申请日：2022-07-29
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Kudum Shinde , Surender Reddy Bhavanam , Weize Kang
CPC classification number: F02C7/32 , F01D5/02 , F01D25/34 , F05D2220/32 , F05D2240/20 , F05D2260/941
Abstract: A gas turbine engine includes a compressor rotor shaft assembly, an accessory gearbox, and a bowed-rotor mitigation drive device drivingly coupled with the accessory gearbox. The bowed-rotor mitigation drive device is driven during an engine startup phase so as to induce a mechanical load (mechanical energy) to the bowed-rotor mitigation drive device. The mechanical load (mechanical energy) is retained within the bowed-rotor mitigation drive device during operation of the gas turbine engine. The mechanical load (mechanical energy) retained within the bowed-rotor mitigation drive device is periodically released by the bowed-rotor mitigation drive device in a plurality of periods so as to provide, in each period, a driving force to the accessory gearbox, which provides the driving force to the compressor rotor shaft assembly to periodically rotate the compressor rotor shaft assembly.
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