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公开(公告)号：US20230272751A1
公开(公告)日：2023-08-31
申请号：US17813677
申请日：2022-07-20
Applicant: General Electric Company
Inventor： David Yamarthi , Paul Mathew , Parmeet Chhabra , Ravindra Shankar Ganiger , Souvik Porel , Gautam Naik , Norman A. Turnquist
CPC classification number: F02C7/36 , F02C7/06 , F05D2250/291 , F05D2260/232 , F05D2260/40311 , F05D2260/96 , F05D2260/98 , F05D2300/612
Abstract: A gearbox assembly for a gas turbine engine includes a hollow gear. The hollow gear has one or more reservoirs configured to store a lubricant and one or more passages configured to supply the lubricant to one or more gear meshes in the gearbox assembly. The hollow gear provides a dampening system configured to absorb vibrations and loading experienced in the gearbox assembly and configured to provide impact resistance for the gearbox assembly.
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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：US20210262350A1
公开(公告)日：2021-08-26
申请号：US16799939
申请日：2020-02-25
Applicant: General Electric Company
Inventor： Paul Mathew , Sriram Krishnamurthy , Shanmuga Priyan Subramanian
Abstract: A rotor blade assembly for a wind turbine includes at least one rotor blade having surfaces defining a pressure side, a suction side, a leading edge, and a trailing edge extending between a blade tip and a blade root. The surfaces are constructed of a polymeric composite material. The rotor blade assembly also includes a protection cap arranged adjacent to one or more of the surfaces of the rotor blade so as to cover at least a portion of the one or more surfaces of the rotor blade. The protection cap includes a body defining an overall length. Further, at least a first segment of the protection cap is constructed of a tungsten-based metal. Thus, the protection cap is configured to reduce erosion and resist corrosion of the rotor blade caused by particle or liquid impact.
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公开(公告)号：US11486349B2
公开(公告)日：2022-11-01
申请号：US16739244
申请日：2020-01-10
Applicant: General Electric Company
Inventor： Vidyashankar Ramasastry Buravalla , Paul Mathew , Sriram Krishnamurthy
IPC: F03D1/06
Abstract: A method for manufacturing a blade structure includes providing the blade structure comprising an outer surface having an aerodynamic profile. The method also includes applying one or more shape memory alloys to the outer surface of the blade structure so as to form an outer protection layer on at least a portion of the blade structure. Moreover, the method includes securing the one or more shape memory alloys to the blade structure.
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公开(公告)号：US11441545B2
公开(公告)日：2022-09-13
申请号：US16799939
申请日：2020-02-25
Applicant: General Electric Company
Inventor： Paul Mathew , Sriram Krishnamurthy , Shanmuga Priyan Subramanian
Abstract: A rotor blade assembly for a wind turbine includes at least one rotor blade having surfaces defining a pressure side, a suction side, a leading edge, and a trailing edge extending between a blade tip and a blade root. The surfaces are constructed of a polymeric composite material. The rotor blade assembly also includes a protection cap arranged adjacent to one or more of the surfaces of the rotor blade so as to cover at least a portion of the one or more surfaces of the rotor blade. The protection cap includes a body defining an overall length. Further, at least a first segment of the protection cap is constructed of a tungsten-based metal. Thus, the protection cap is configured to reduce erosion and resist corrosion of the rotor blade caused by particle or liquid impact.
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Patent Agency Ranking
公开(公告)号：US20220280998A1
公开(公告)日：2022-09-08
申请号：US17473281
申请日：2021-09-13
Applicant: General Electric Company
Inventor： Paul Mathew , Mohandas Nayak , Sathisha Chikkabikkodu Hanum , Monty Lee Shelton
Abstract: An anti-fretting coating composition that is operationally stable at temperatures of 800° F. to 2650° F. is provided. The anti-fretting coating composition primarily includes cobalt and aluminum oxide and may also include other modifying phases that enhance the overall tribological performance. A component coated with the anti-fretting coating composition is also provided. The component includes a substrate having a first contact surface shaped to cooperate with a second contact surface of an abutting member in a manner which can develop wear between the first contact surface and the second contact surface. The first contact surface includes an anti-fretting coating thereon formed from the disclosed anti-fretting coating composition.
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公开(公告)号：US10774670B2
公开(公告)日：2020-09-15
申请号：US15974821
申请日：2018-05-09
Applicant: General Electric Company
Inventor： Paul Mathew , Mohandas Nayak , Krishnendu Saha , Deoras Prabhudharwadkar
Abstract: A filled abradable seal component, an associated method of manufacturing, and a turbomachine including the filled abradable seal component are disclosed. The method includes positioning the abradable seal component including a plurality of honeycomb cells, applying a filler material on the abradable seal component to fill the plurality of honeycomb cells, and curing the filler material at a temperature below 250 degrees Celsius to produce the filled abradable seal component. The filler material includes an abradable material, a binder material, and a fluid catalyst. The abradable material includes at least one of nickel chromium aluminum-bentonite, cobalt nickel chromium aluminum yttrium-polyester, cobalt nickel chromium aluminum yttrium-boron nitride, aluminum silicon-bentonite, aluminum bronze-polyester, nickel graphite, or aluminum silicon-boron nitride. The binder material includes at least one of aluminum, nickel-aluminum, aluminum thiophosphate, or aluminum thiosulfate. The fluid catalyst includes a solvent having hydroxyl groups.
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公开(公告)号：US12258909B2
公开(公告)日：2025-03-25
申请号：US17813677
申请日：2022-07-20
Applicant: General Electric Company
Inventor： David Yamarthi , Paul Mathew , Parmeet Chhabra , Ravindra Shankar Ganiger , Souvik Porel , Gautam Naik , Norman A. Turnquist
Abstract: A gearbox assembly for a gas turbine engine includes a hollow gear. The hollow gear has one or more reservoirs configured to store a lubricant and one or more passages configured to supply the lubricant to one or more gear meshes in the gearbox assembly. The hollow gear provides a dampening system configured to absorb vibrations and loading experienced in the gearbox assembly and configured to provide impact resistance for the gearbox assembly.
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公开(公告)号：US20240044254A1
公开(公告)日：2024-02-08
申请号：US17881771
申请日：2022-08-05
Applicant: General Electric Company
Inventor： David Raju Yamarthi , Vasanth Kumar Balaramudu , Vishnu Vardhan Venkata Tatiparthi , Paul Mathew , Douglas Lorrimer Armstrong , Gary Willard Bryant, JR. , Nuthi Srinivas
CPC classification number: F01D5/147 , F01D5/282 , F05D2250/25 , F05D2240/30 , F05D2300/612 , F05D2300/6034
Abstract: An airfoil assembly and a method of manufacturing the same are provided, the airfoil assembly defining a span axis, a root end, and a tip end. The airfoil assembly includes a reinforcement structure comprising a first helical support structure wrapped around the span axis between the root end and the tip end and a second helical support structure wrapped around the span axis between the root end and the tip end; a polymeric matrix material positioned at least partially around the reinforcement structure; and an outer skin positioned around the reinforcement structure and the polymeric matrix material.
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公开(公告)号：US20240011410A1
公开(公告)日：2024-01-11
申请号：US17889899
申请日：2022-08-17
Applicant: General Electric Company
Inventor： Pankaj Dhaka , Paul Mathew , Ravindra Shankar Ganiger , Gautam Naik
IPC: F01D11/24
CPC classification number: F01D11/24 , F05D2220/32 , F05D2240/55 , F05D2260/60
Abstract: Disclosed herein are example variable flowpath casings for blade tip clearance control. An example casing for a turbine engine includes a first annular substrate extending along an axial direction, the first annular substrate defining a cavity at a radially inward surface of the first annular substrate, a second annular substrate positioned at least partially within the cavity of the first annular substrate, and a tension belt extending circumferentially around a periphery of the second annular substrate.
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