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公开(公告)号：US20210199025A1
公开(公告)日：2021-07-01
申请号：US16731606
申请日：2019-12-31
Applicant: General Electric Company
Inventor： Deoras Prabhudharwadkar , Jalal Hunain Zia , Majed Sammak
Abstract: A power generation system includes a combustion system, a turbocharger, and a heat recovery system. The combustion system is configured to combust a fuel with a flow of air. The combustion system is further configured to generate an exhaust stream. The turbocharger is configured to compress a flow of compressed air and to channel the flow of compressed air to the combustion system. The combustion system is configured to combust the fuel with the flow of compressed air and an additional flow of air. The heat recovery system is configured to recover heat from the exhaust stream and to drive the turbocharger. The heat recovery system uses a supercritical working fluid to absorb heat from the exhaust stream and to drive the turbocharger.
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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：US20180372112A1
公开(公告)日：2018-12-27
申请号：US15629036
申请日：2017-06-21
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Deoras Prabhudharwadkar , David Richard Johns
Abstract: A turbomachine and a heat exchange system for the turbomachine are disclosed. The turbomachine includes a stationary component, a rotatable component, an abradable seal component, and a plurality of heat dissipating elements. The rotatable component includes teeth. The abradable seal component is operatively coupled to a surface of the stationary component and disposed facing the teeth to define a clearance there between the abradable seal component and the rotatable component. The plurality of heat dissipating elements is coupled to the abradable seal component. Each of the plurality of heat dissipating elements extends from the abradable seal component through the surface of the stationary component to a turbomachine cavity.
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公开(公告)号：US10690251B2
公开(公告)日：2020-06-23
申请号：US15696489
申请日：2017-09-06
Applicant: General Electric Company
Inventor： Krishnendu Saha , Deoras Prabhudharwadkar , Ashok Gopinath
Abstract: Labyrinth seal system includes stationary component and rotatable component, where one of the stationary and rotatable components includes teeth. The labyrinth seal system further includes abradable component coupled to surface of other of the stationary and rotatable components and disposed facing the teeth. The abradable component includes a plurality of honeycomb cells disposed adjacent to each other along axial direction and circumferential direction. Each honeycomb cell includes a plurality of radial sidewalls, where each radial sidewall includes first portion and second portion. The first portion is coupled to the surface and the second portion extends from the first portion towards clearance defined between the stationary and rotatable components. The second portion is bent relative to radial axis of the labyrinth seal system.
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Patent Agency Ranking
公开(公告)号：US11047265B1
公开(公告)日：2021-06-29
申请号：US16731606
申请日：2019-12-31
Applicant: General Electric Company
Inventor： Deoras Prabhudharwadkar , Jalal Hunain Zia , Majed Sammak
Abstract: A power generation system includes a combustion system, a turbocharger, and a heat recovery system. The combustion system is configured to combust a fuel with a flow of air. The combustion system is further configured to generate an exhaust stream. The turbocharger is configured to compress a flow of compressed air and to channel the flow of compressed air to the combustion system. The combustion system is configured to combust the fuel with the flow of compressed air and an additional flow of air. The heat recovery system is configured to recover heat from the exhaust stream and to drive the turbocharger. The heat recovery system uses a supercritical working fluid to absorb heat from the exhaust stream and to drive the turbocharger.
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公开(公告)号：US10815874B2
公开(公告)日：2020-10-27
申请号：US16225825
申请日：2018-12-19
Applicant: General Electric Company
Inventor： Jalal Hunain Zia , Deoras Prabhudharwadkar , Christopher Joseph Homison , Maruthi Manohar Jupudi
IPC: F02B37/10 , F02B37/013 , F01K23/10 , F02C6/18 , F02B37/007 , F02C6/12 , F02C7/10 , F02C7/143 , F02C9/16 , F02C9/28
Abstract: A turbocharger system includes a low pressure turbocharger (LPT) that includes an LPT compressor and an LPT turbine. The turbocharger system is configured to divide ambient air compressed by the LPT compressor into a heat exchanger flow and an HPT compressor inlet flow. The turbocharger system also includes a high pressure turbocharger (HPT) that includes an HPT compressor and an HPT turbine. The HPT compressor is configured to further compress the HPT compressor inlet flow, which is then channeled to a rotary machine as auxiliary compressed air. The turbocharger system further includes a heat exchanger configured to place the heat exchanger flow into thermal communication with exhaust gases associated with the rotary machine. The discharged heat exchanger flow is divided into parallel streams, and the LPT turbine and the HPT turbine are each configured to be driven by a respective one of the parallel streams.
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公开(公告)号：US20190353102A1
公开(公告)日：2019-11-21
申请号：US15979866
申请日：2018-05-15
Applicant: General Electric Company
Inventor： Maruthi Manohar Jupudi , Bradly Aaron Kippel , Ashok Kumar Balumuri , Majed Sammak , Jalal Hunain Zia , Deoras Prabhudharwadkar
Abstract: An evaporative cooling system for a gas turbine includes a first plurality of evaporative cooling media, spaced from the other evaporative cooling media. The system also includes a plurality of valves, with water flowing through at least one valve to fully wet at least one evaporative cooling medium. In one mode of operation, at least one evaporative cooling medium remains dry.
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公开(公告)号：US11828230B2
公开(公告)日：2023-11-28
申请号：US17492737
申请日：2021-10-04
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Maruthi Manohar Jupudi , Paul Mathew , Jose Antonio Cuevas Alvarez , Bouria Mohamed Faqihi , Deoras Prabhudharwadkar , Murali Krishna Kalaga
Abstract: Mitigating particulate intrusion to an air intake system of a gas turbine system with intrusion protective coatings tailored to locale of operation. A particulate intrusion protective coating is applied to a surface of a component of the air intake system to mitigate ingress of particulates within the air intake system and the gas turbine system. The particulate intrusion protective coating includes one or more particulate ingress influencing properties tailored to the common attributes of the particulates associated with the locale of operation of the gas turbine engine and the air intake system. The particulate ingress influencing properties affect rebounding and coalescing characteristics of the particulates at a point of impact with the applied surface having the particulate intrusion protective coating, entraining the particulates at the point of impact and inhibiting further ingress along an inlet air flow path of the air intake system into the gas turbine engine.
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公开(公告)号：US10961909B2
公开(公告)日：2021-03-30
申请号：US15979866
申请日：2018-05-15
Applicant: General Electric Company
Inventor： Maruthi Manohar Jupudi , Bradly Aaron Kippel , Ashok Kumar Balumuri , Majed Sammak , Jalal Hunain Zia , Deoras Prabhudharwadkar
Abstract: An evaporative cooling system for a gas turbine includes a first plurality of evaporative cooling media, spaced from the other evaporative cooling media. The system also includes a plurality of valves, with water flowing through at least one valve to fully wet at least one evaporative cooling medium. In one mode of operation, at least one evaporative cooling medium remains dry.
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