Patents by Inventor Deoras PRABHUDHARWADKAR
Deoras PRABHUDHARWADKAR has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 11828230Abstract: 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.Type: GrantFiled: October 4, 2021Date of Patent: November 28, 2023Assignee: GENERAL ELECTRIC COMPANYInventors: Maruthi Manohar Jupudi, Paul Mathew, Jose Antonio Cuevas Alvarez, Bouria Mohamed Faqihi, Deoras Prabhudharwadkar, Murali Krishna Kalaga
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Publication number: 20230227764Abstract: An impeller, for example, a Rushton impeller for a bioreactor system is disclosed. The impeller includes a hub, optionaly including a slot, a plurality of blades, and one or more turbulators. The plurality of blades is disposed along a circumferential direction of the hub and spaced apart from each other. Each of the plurality of blades is coupled to at least a portion of a circumference and/or a top surface of the hub. Each blade of the plurality of blades includes a pressure face and a suction face. The one or more turbulators is disposed on at least a portion of the suction face, the pressure face, or both, of a blade of the plurality of blades.Type: ApplicationFiled: February 28, 2023Publication date: July 20, 2023Applicant: GLOBAL LIFE SCIENCES SOLUTIONS USA LLCInventors: DEORAS PRABHUDHARWADKAR, ASHOK GOPINATH
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Patent number: 11629322Abstract: An impeller, for example, a Rushton impeller for a bioreactor system is disclosed. The impeller includes a hub, optionally including a slot, a plurality of blades, and one or more turbulators. The plurality of blades is disposed along a circumferential direction of the hub and spaced apart from each other. Each of the plurality of blades is coupled to at least a portion of a circumference and/or a top surface of the hub. Each blade of the plurality of blades includes a pressure face and a suction face. The one or more turbulators is disposed on at least a portion of the suction face, the pressure face, or both, of a blade of the plurality of blades.Type: GrantFiled: December 4, 2017Date of Patent: April 18, 2023Assignee: GLOBAL LIFE SCIENCES SOLUTIONS USA LLCInventors: Deoras Prabhudharwadkar, Ashok Gopinath
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Publication number: 20230108653Abstract: 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.Type: ApplicationFiled: October 4, 2021Publication date: April 6, 2023Applicant: GENERAL ELECTRIC COMPANYInventors: MARUTHI MANOHAR JUPUDI, PAUL MATHEW, JOSE ANTONIO CUEVAS ALVAREZ, BOURIA MOHAMED FAQIHI, DEORAS PRABHUDHARWADKAR, MURALI KRISHNA KALAGA
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Publication number: 20210396156Abstract: Disclosed is an exhaust duct (1) for a gas turbine engine (50), comprising a silencer section (12). At least two plate-shaped silencer baffles (20) are provided inside the silencer section (12). At least one of the plate-shaped silencer baffles is configured as a heat exchange device in that it comprises at least one internal cavity (22) suitable for receiving a heat exchange fluid and leakproof with respect to the interior of the exhaust duct, wherein the at least one internal cavity is fluidly connected to the outside of the exhaust duct at an inlet port and an outlet port (23, 24). This device is useful for recuperating exhaust heat from exhaust gases of the gas turbine engine without the expense and additional space required for providing a heat recovery steam generator.Type: ApplicationFiled: June 18, 2021Publication date: December 23, 2021Inventors: Bouria Mohamed FAQIHI, Deoras PRABHUDHARWADKAR, Jalal ZIA, Fadi GHAITH
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Publication number: 20210199025Abstract: 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.Type: ApplicationFiled: December 31, 2019Publication date: July 1, 2021Inventors: Deoras Prabhudharwadkar, Jalal Hunain Zia, Majed Sammak
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Patent number: 11047265Abstract: 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.Type: GrantFiled: December 31, 2019Date of Patent: June 29, 2021Assignee: General Electric CompanyInventors: Deoras Prabhudharwadkar, Jalal Hunain Zia, Majed Sammak
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Patent number: 10961909Abstract: 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.Type: GrantFiled: May 15, 2018Date of Patent: March 30, 2021Assignee: General Electric CompanyInventors: Maruthi Manohar Jupudi, Bradly Aaron Kippel, Ashok Kumar Balumuri, Majed Sammak, Jalal Hunain Zia, Deoras Prabhudharwadkar
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Patent number: 10815874Abstract: 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.Type: GrantFiled: December 19, 2018Date of Patent: October 27, 2020Assignee: General Electric CompanyInventors: Jalal Hunain Zia, Deoras Prabhudharwadkar, Christopher Joseph Homison, Maruthi Manohar Jupudi
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Patent number: 10774670Abstract: 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.Type: GrantFiled: May 9, 2018Date of Patent: September 15, 2020Assignee: GENERAL ELECTRIC COMPANYInventors: Paul Mathew, Mohandas Nayak, Krishnendu Saha, Deoras Prabhudharwadkar
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Patent number: 10690251Abstract: 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.Type: GrantFiled: September 6, 2017Date of Patent: June 23, 2020Assignee: General Electric CompanyInventors: Krishnendu Saha, Deoras Prabhudharwadkar, Ashok Gopinath
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Publication number: 20190353102Abstract: 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.Type: ApplicationFiled: May 15, 2018Publication date: November 21, 2019Applicant: General Electric CompanyInventors: Maruthi Manohar Jupudi, Bradly Aaron Kippel, Ashok Kumar Balumuri, Majed Sammak, Jalal Hunain Zia, Deoras Prabhudharwadkar
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Publication number: 20190345433Abstract: An impeller (18), for example, a Rushton impeller for a bioreactor system (10) is disclosed. The impeller (18) includes a hub (44), optionaly including a slot (168), a plurality of blades (46), and one or more turbulators (64). The plurality of blades (46) is disposed along a circumferential direction (48) of the hub (44) and spaced apart from each other. Each of the plurality of blades (46) is coupled to at least a portion of a circumference (50) and/or a top surface (1351;1451;1551) of the hub (44). Each blade of the plurality of blades (46) includes a pressure face (52) and a suction face (54). The one or more turbulators (64) is disposed on at least a portion of the suction face (54), the pressure face (52), or both, of a blade of the plurality of blades (46).Type: ApplicationFiled: December 4, 2017Publication date: November 14, 2019Applicant: GENERAL ELECTRIC COMPANYInventors: DEORAS PRABHUDHARWADKAR, ASHOK GOPINATH
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Publication number: 20190195131Abstract: 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.Type: ApplicationFiled: December 19, 2018Publication date: June 27, 2019Inventors: Jalal Hunain ZIA, Deoras PRABHUDHARWADKAR, Christopher Joseph HOMISON, Maruthi Manohar JUPUDI
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Publication number: 20180372112Abstract: 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.Type: ApplicationFiled: June 21, 2017Publication date: December 27, 2018Inventors: Deoras Prabhudharwadkar, David Richard Johns
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Publication number: 20180355745Abstract: 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.Type: ApplicationFiled: May 9, 2018Publication date: December 13, 2018Inventors: Paul MATHEW, Mohandas NAYAK, Krishnendu SAHA, Deoras PRABHUDHARWADKAR
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Publication number: 20180087669Abstract: 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.Type: ApplicationFiled: September 6, 2017Publication date: March 29, 2018Inventors: Krishnendu SAHA, Deoras PRABHUDHARWADKAR, Ashok GOPINATH