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公开(公告)号：US11703225B2
公开(公告)日：2023-07-18
申请号：US17663311
申请日：2022-05-13
Applicant: General Electric Company
Inventor： Saket Singh , Pradeep Naik , Rimple Rangrej , Shai Birmaher , Ranganatha Narasimha Chiranthan , Ajoy Patra , Ravindra Shankar Ganiger , Hiranya Nath
Abstract: A combustor liner for a combustor of a gas turbine includes an outer liner extending circumferentially about a combustor centerline, and an inner liner extending circumferentially about the combustor centerline, where the outer liner and the inner liner define a combustion chamber therebetween. At least one of the outer liner and the inner liner includes a dilution flow assembly comprising, (a) an annular slot dilution opening, and (b) a dilution fence extending between an upstream side of the annular slot dilution opening to a downstream side of the annular slot dilution opening, and extending into the combustion chamber, the dilution fence including a plurality of dilution openings therethrough for providing a flow of an oxidizer through the dilution fence into the combustion chamber.
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公开(公告)号：US11668462B1
公开(公告)日：2023-06-06
申请号：US17664976
申请日：2022-05-25
Applicant: General Electric Company
Inventor： Michael A. Benjamin , Ravindra Shankar Ganiger , Hiranya Nath
CPC classification number: F23R3/002 , F23R3/50 , F23R3/08 , F23R2900/00001 , F23R2900/03341
Abstract: A method of operating a combustor of a gas turbine, the combustor including a combustor liner that defines a total combustion chamber volume, and has a primary combustion zone defining a primary volume. The combustor liner includes a movable portion that is arranged to be actuated to adjust a percentage of the primary volume with respect to the total combustion chamber volume. The method includes, at a first operating state of the gas turbine, adjusting a size of the primary volume to a first percentage of the total combustion chamber volume by actuating the movable portion to adjust the size of the primary volume, and at a second operating state of the gas turbine different from the first operating state, adjusting the size of the primary volume to a second percentage of the total combustion chamber volume by actuating the movable portion to adjust the size of the primary volume.
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公开(公告)号：US11661891B1
公开(公告)日：2023-05-30
申请号：US17814334
申请日：2022-07-22
Applicant: General Electric Company
Inventor： Narayanan Janakiraman , Paul Mathew , Sreerama Prasad Ramaswamy , Hiranya Nath , Ravindra Shankar Ganiger
CPC classification number: F02C7/30 , F02C7/222 , F05D2220/323 , F05D2260/95 , F05D2300/505 , F05D2300/6111
Abstract: A component susceptible to the formation of deposits, such as a component of a hydrocarbon system in a gas turbine engine. The component includes a substrate having a surface susceptible to the formation of a deposit thereon. A shape memory alloy coating is formed on the surface of the substrate. The shape memory alloy coating is a plurality of particles formed on the surface, and each particle of the plurality of particles is formed from a shape memory alloy.
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公开(公告)号：US11655724B1
公开(公告)日：2023-05-23
申请号：US17840293
申请日：2022-06-14
Applicant: General Electric Company
Inventor： Venkata Jayateja Nedunuri , Abhijeet Yadav , Shawn P. Riley , Richa Awasthi , Nilesh Vilas Varote , Ravindra Shankar Ganiger , Anusrita Raychaudhuri
IPC: F01D11/22
CPC classification number: F01D11/22 , F05D2220/323 , F05D2240/515
Abstract: Clearance control systems with electromagnetic actuators are disclosed. An example electromagnetically-actuated clearance control system for a gas turbine engine comprises an electromagnetic coil coupled to a first end of a facesheet, the electromagnetic coil to generate a magnetic field in response to a connection of a power supply, a ferromagnetic sheet coupled to a second end of the facesheet, the ferromagnetic sheet drawn radially-inward toward the electromagnetic coil when the magnetic field is generated, a first end of the ferromagnetic sheet coupled to a first compression spring and a second end of the ferromagnetic sheet coupled to a second compression spring, the first and second compression springs to compress in response to the ferromagnetic sheet being drawn radially-inward.
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公开(公告)号：US11591932B2
公开(公告)日：2023-02-28
申请号：US17387002
申请日：2021-07-28
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Praveen Sharma , Shivam Mittal , Bhujabal Prashant Mahadeo , Weize Kang , Richard Schmidt
IPC: F01D25/16 , F02C7/36 , F01D25/18 , F03G7/06 , F02C7/06 , F16C27/04 , F16C35/077 , F16C19/26 , F16C19/06
Abstract: A casing for a bearing of a gas turbine engine includes a shaft extending along an axial direction. The casing includes an attachment feature at a radially outermost portion of the casing. The attachment feature is configured to be coupled to a static frame of the gas turbine engine. The casing further includes a plurality of support arms extend from the attachment feature to a radially innermost portion of the casing. At least one support arm of the plurality of support arms defines an internal cavity. Further, the radially innermost portion of the casing is configured to be coupled to an outer race of the bearing. The casing additionally includes a reinforcing member housed at least partially within the internal cavity of at least one support arm. Moreover, the reinforcing member includes a shape memory alloy material.
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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：US11420755B2
公开(公告)日：2022-08-23
申请号：US16535315
申请日：2019-08-08
Applicant: General Electric Company
Inventor： Praveen Sharma , Vinod Shashikant Chaudhari , Sivakumar Mahesh , Bhujabal Prashant Mahadeo , Mohan Kannaiah Raju , Ravindra Shankar Ganiger , Jagadisha Pai Nagarmat , Shivam Mittal
Abstract: A vibration isolation system for a gas turbine engine. The vibration isolation system includes a first fixed structure and a second fixed structure separate from the first fixed structure. The vibration isolation system further includes a connector coupling the first fixed structure to the second fixed structure. Additionally, the vibration isolation system includes an isolator, including a shape memory alloy material, associated with the connector. The isolator is arranged between the first fixed structure and the second fixed structure such that the isolator reduces vibrations transferred between the first fixed structure and the second fixed structure.
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公开(公告)号：US20220178270A1
公开(公告)日：2022-06-09
申请号：US17115366
申请日：2020-12-08
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Ravindra Shankar Ganiger , Kevin Lee Kirkeng , Vishnu Das K , Reddi Hari Prasad Reddy Mylapalli
IPC: F01D17/16
Abstract: Variable stator vanes with anti-lock trunnions are disclosed. An example apparatus disclosed herein includes an airfoil to be disposed within a flow path of a gas turbine engine, the gas turbine engine defining an axial axis, a radial axis and a circumferential axis, an outer trunnion, and an inner trunnion including a curved surface in an axial-radial plane, the inner trunnion enabling the airfoil to be rotatably mounted to an inner shroud of the gas turbine engine.
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公开(公告)号：US11261787B2
公开(公告)日：2022-03-01
申请号：US16015468
申请日：2018-06-22
Applicant: GENERAL ELECTRIC COMPANY
Abstract: An aircraft can include a turbine engine including a rotor and a stator, and also including a compressor, a combustor, and a turbine in axial flow arrangement. The aircraft can further include an anti-icing system with a magnetic field generator having a rotating portion and a non-rotating portion, as well as an array of carbon nanotubes thermally coupled to an exposed surface.
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公开(公告)号：US20210277800A1
公开(公告)日：2021-09-09
申请号：US17329220
申请日：2021-05-25
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Praveen Sharma , Bhujabal Prashant Mahadeo , Shivam Mittal
Abstract: A support assembly for a bearing of a gas turbine engine includes a shaft extending along an axial direction. The support assembly includes an outer race positioned radially exterior to the bearing such that the outer race supports the bearing. Additionally, the support assembly includes a shape memory alloy damper positioned radially exterior to the outer race and at least partially supporting the outer race. Moreover, the shape memory alloy damper includes a plurality of sleeves. One or more sleeves of the plurality of sleeves include a shape memory alloy material.
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