Patents by Inventor Krishnamoorthi Sivalingam
Krishnamoorthi Sivalingam 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: 11834987Abstract: A propulsion system for use with an aircraft includes a gas turbine engine, an electric power system, and at least one propulsor. The gas turbine engine includes a compressor, a combustor, and a turbine. The electric power system includes a generator coupled to the gas turbine engine to generate electrical energy, power electronics connected to the generator to receive the electrical energy from the generator, and a motor configured to produce rotational energy in response to receiving electric energy from the power electronics. The propulsor is configured to use rotational energy received from the motor of the electric power system to generate thrust for propelling the aircraft.Type: GrantFiled: March 16, 2021Date of Patent: December 5, 2023Assignee: Rolls-Royce CorporationInventors: John P. E. Forsdike, Krishnamoorthi Sivalingam, Palanisamy Mohan Kumar, Rakesh Murali
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Patent number: 11807381Abstract: A hybrid propulsion system for use with an aircraft includes a gas turbine engine, at least one propulsor, and an electric power system. The electric power system is coupled to the gas turbine engine to generate electrical energy and the propulsor to provide electrical energy to drive the propulsor. The electric power system includes a thermal management system configured to cool a heat load generated by the electric power system.Type: GrantFiled: March 16, 2021Date of Patent: November 7, 2023Assignee: Rolls-Royce CorporationInventors: Krishnamoorthi Sivalingam, Chandana J. Gajanayake, Jeyaraman Kumaravel, Palanisamy Mohan Kumar, Govind Pandey, Yunzhe Zhai, Divya Bharathi Perumal
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Patent number: 11799162Abstract: An aerospace battery may include a housing, a retaining seat disposed in the housing, and a battery pack core supported by the retaining seat in the housing. The battery pack core may include at least one cell district comprising a plurality of pouch cell batteries and at least one flexible cold plate disposed between at least two adjacent pouch cell batteries of the plurality of pouch cell batteries. The retaining seat may define a fluid delivery channel configured to couple to an inlet of a cooling channel of the flexible cold plate and a fluid return channel configured to couple to an outlet of the cooling channel of the flexible cold plate.Type: GrantFiled: August 18, 2021Date of Patent: October 24, 2023Assignees: Rolls-Royce Singapore Pte. Ltd., Rolls-Royce plcInventors: Michael Adam Zagrodnik, Teh Yee Siang, Mathivanan Anand Prabhu, Krishnamoorthi Sivalingam, Stephen Mountain
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Publication number: 20230054839Abstract: An aerospace battery may include a housing and a battery pack core. The housing may include a thin dual layer casing. The battery pack core is disposed in the housing and may include at least one cell district that includes a plurality of pouch cell batteries. A ceramic material may surround the at least one cell district and a closed cell foam may fill open space between the ceramic material and the housing.Type: ApplicationFiled: August 18, 2021Publication date: February 23, 2023Inventors: Michael Adam Zagrodnik, Teh Yee Siang, Mathivanan Anand Prabhu, Krishnamoorthi Sivalingam, Stephen Mountain
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Publication number: 20230059778Abstract: An aerospace battery may include a housing, a retaining seat disposed in the housing, and a battery pack core supported by the retaining seat in the housing. The battery pack core may include at least one cell district comprising a plurality of pouch cell batteries and at least one flexible cold plate disposed between at least two adjacent pouch cell batteries of the plurality of pouch cell batteries. The retaining seat may define a fluid delivery channel configured to couple to an inlet of a cooling channel of the flexible cold plate and a fluid return channel configured to couple to an outlet of the cooling channel of the flexible cold plate.Type: ApplicationFiled: August 18, 2021Publication date: February 23, 2023Inventors: Michael Adam Zagrodnik, Teh Yee Siang, Mathivanan Anand Prabhu, Krishnamoorthi Sivalingam, Stephen Mountain
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Publication number: 20220402620Abstract: An aircraft including a battery pack having a plurality of battery cells arranged to vent into a venting region of the battery pack. A path is defined between the venting region and an exterior of the aircraft, whereby thermal products vented by the cells can exit the aircraft via the path. In some embodiments, the venting region is or is in fluid communication with an air channel through which air flows from an aircraft air inlet to an aircraft air outlet. In other embodiments, the path joins the venting region and an opening in an external surface of the aircraft.Type: ApplicationFiled: May 23, 2022Publication date: December 22, 2022Applicant: ROLLS-ROYCE plcInventors: Michael Adam ZAGRODNIK, Krishnamoorthi SIVALINGAM, Satyanarayana Reddy GAJJELA, Vidor VERES-SZEKELY, Daniel LORINCZ, István ÖRÖKÖS-TÓTH, Anand Prabhu MATHIVANAN
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Publication number: 20220402402Abstract: Aircraft with battery thermal regulation systems, including: an aircraft air inlet and an aircraft air outlet; a battery pack including battery cells; and a battery thermal regulation system including a first air channel, a surface of which is in thermal communication with the battery cells so that air flowing through the first air channel exchanges heat with the cells through the surface; and an airflow device for driving an airflow. The battery thermal regulation system has a first and a second mode operation. In the first mode, the first air channel is fluidly connected with the aircraft air inlet and the aircraft air outlet whereby, during flight of the aircraft, air can enter the aircraft through the air inlet, flow through the first air channel and exit the aircraft through the air outlet. In the second mode, the airflow device drives an airflow through the first air channel.Type: ApplicationFiled: May 23, 2022Publication date: December 22, 2022Applicant: ROLLS-ROYCE plcInventors: Michael Adam ZAGRODNIK, Krishnamoorthi SIVALINGAM, Satyanarayana Reddy GAJJELA, Vidor VERES-SZÉKELY, Daniel LORINCZ, István ÖRÖKÖS-TÓTH, Anand Prabhu MATHIVANAN, Umesh MAHAJAN, Rakesh MURALI
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Publication number: 20220407135Abstract: Methods for thermally regulating batteries of aircraft are provided. The aircraft comprises: an air inlet; an air outlet; a battery pack comprising battery cells; and an air channel in fluid communication with the air inlet and the air outlet, a surface of the air channel being in thermal communication with the battery cells whereby air flowing through the air channel exchanges heat with the battery cells through the surface of the air channel. The methods comprise: connecting an external supply of air to the air inlet of the aircraft; and delivering a flow of air through the air channel using the external supply of air. A kit comprising the aircraft and the external supply of air is also provided.Type: ApplicationFiled: May 23, 2022Publication date: December 22, 2022Applicant: ROLLS-ROYCE plcInventors: Michael Adam ZAGRODNIK, Krishnamoorthi SIVALINGAM, Satyanarayana Reddy GAJJELA, Vidor VERES-SZEKELY, Daniel LORINCZ, István ÖRÖKÖS-TÓTH, Anand Prabhu MATHIVANAN, Umesh MAHAJAN, Rakesh MURALI
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Publication number: 20220407144Abstract: Battery packs for aircraft are provided, as are aircraft comprising such battery packs. One such battery pack comprises: a housing enclosing a plurality of battery cells; and an air channel. The air channel is connectable to an aircraft air inlet and an aircraft air outlet whereby, during flight of the aircraft, air enters the aircraft through the air inlet, passes through the battery pack air channel and exits the aircraft through the air outlet. At least a portion of a surface of the air channel is in thermal contact with the battery cells, whereby air flowing through the air channel exchanges heat with the battery cells through the surface of the air channel without entering the housing and contacting the battery cells.Type: ApplicationFiled: May 23, 2022Publication date: December 22, 2022Applicant: ROLLS-ROYCE PLCInventors: Michael Adam ZAGRODNIK, Krishnamoorthi SIVALINGAM, Satyanarayana Reddy GAJJELA, Vidor VERES-SZÉKELY, Dániel LÖRINCZ, István ÖRÖKÖS-TÓTH, Anand Prabhu MATHIVANAN
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Publication number: 20220328914Abstract: A battery housing for an aerospace battery may include a first endplate; a flange; and an elliptical cylinder extending from a first cylinder end to a second cylinder end. The first cylinder end of the elliptical cylinder may be welded to the first endplate, and the second cylinder end of the elliptical cylinder may be welded to the flange. The elliptical cylinder is formed from a sheet of material comprising a first sheet end and a second sheet end. The first sheet end may be welded to the second sheet end at a weld location that runs from the first cylinder end to the second cylinder end at a perimeter location that is calculated to experience a reduced stress during pressurization of the housing.Type: ApplicationFiled: April 9, 2021Publication date: October 13, 2022Inventors: Michael Adam Zagrodnik, Stephen Mountain, Peter Schenk, Mathivanan Anand Prabhu, Krishnamoorthi Sivalingam, Teh Yee Siang, Chandana Jayampathi Gajanayake, Melvin Yang Yueng Yap
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Publication number: 20220328913Abstract: An aerospace battery may include a housing; a battery pack core; a ceramic felt surrounding at least part of the battery pack core; and a closed cell foam filling open space between the battery pack core, the ceramic felt, and the housing.Type: ApplicationFiled: April 9, 2021Publication date: October 13, 2022Inventors: Michael Adam Zagrodnik, Stephen Mountain, Peter Schenk, Mathivanan Anand Prabhu, Krishnamoorthi Sivalingam, Teh Yee Siang, Chandana Jayampathi Gajanayake, Melvin Yang Yueng Yap
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Publication number: 20220328916Abstract: A battery pack core may include a cold plate comprising a plurality of apertures defined between a first major surface and a second major surface of the cold plate; a plurality of battery cells, a single battery cell positioned in each aperture of the plurality of apertures such that a first end of the battery cell projects beyond the first major surface and a second end of the battery cell projects beyond the second major surface; and a plurality of silicone bushings, a silicone bushing surrounding each battery cell of the plurality of battery cells and contacting a wall of the aperture in which the battery cell is positioned.Type: ApplicationFiled: April 9, 2021Publication date: October 13, 2022Inventors: Michael Adam Zagrodnik, Stephen Mountain, Peter Schenk, Mathivanan Anand Prabhu, Krishnamoorthi Sivalingam, Teh Yee Siang, Chandana Jayampathi Gajanayake, Melvin Yang Yueng Yap
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Publication number: 20220297848Abstract: A hybrid propulsion system for use with an aircraft includes a gas turbine engine, at least one propulsor, and an electric power system. The electric power system is coupled to the gas turbine engine to generate electrical energy and the propulsor to provide electrical energy to drive the propulsor. The electric power system includes a thermal management system configured to cool a heat load generated by the electric power system.Type: ApplicationFiled: March 16, 2021Publication date: September 22, 2022Inventors: Krishnamoorthi Sivalingam, Chandana J. Gajanayake, Jeyaraman Kumaravel, Palanisamy Mohan Kumar, Govind Pandey, Yunzhe Zhai, Divya Bharathi Perumal
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Publication number: 20220298968Abstract: A propulsion system for use with an aircraft includes a gas turbine engine, an electric power system, and at least one propulsor. The gas turbine engine includes a compressor, a combustor, and a turbine. The electric power system includes a generator coupled to the gas turbine engine to generate electrical energy, power electronics connected to the generator to receive the electrical energy from the generator, and a motor configured to produce rotational energy in response to receiving electric energy from the power electronics. The propulsor is configured to use rotational energy received from the motor of the electric power system to generate thrust for propelling the aircraft.Type: ApplicationFiled: March 16, 2021Publication date: September 22, 2022Inventors: John P.E. Forsdike, Krishnamoorthi Sivalingam, Palanisamy Mohan Kumar, Rakesh Murali
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Patent number: 9074582Abstract: The present invention relates to a wind turbine nacelle having a top face with a longitudinal extension in a wind direction. The nacelle comprises a cooling device having a cooling area and extending from the first face of the nacelle, and a cover having at least one inner face and at least a front edge facing the wind direction. The cooling device is enclosed by the first face of the nacelle and the inner face of the cover and is arranged in a front distance of at least 440 mm from the front edge of the cover.Type: GrantFiled: January 29, 2010Date of Patent: July 7, 2015Assignee: Vestas Wind Systems A/SInventors: Krishnamoorthi Sivalingam, Anand Bahuguni, Ravi Kandasamy, Srikanth Narasimalu, John K. Grevsen, Jesper Nyvad, Paul T. Tietze
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Patent number: 9039369Abstract: The present invention relates to a wind turbine nacelle having a top face with a longitudinal extension in a wind direction, comprising a cooling device extending from the top face of the nacelle and a cover having at least one inner face. The cooling device is enclosed by the top face of the nacelle and the inner face of the cover.Type: GrantFiled: January 29, 2010Date of Patent: May 26, 2015Assignee: Vestas Wind Systems A/SInventors: Krishnamoorthi Sivalingam, Anand Bahuguni, Ravi Kandasamy, Srikanth Narasimalu, John K. Grevsen, Jesper Nyvad, Paul T. Tietze
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Patent number: 9039368Abstract: The present invention relates to a wind turbine nacelle having a first face with a longitudinal extension in a wind direction, comprising a cooling device having a cooling area and extending from the first face of the nacelle, and a cover having at least one inner face, the cooling device being enclosed by the first face of the nacelle and the inner face of the cover. A first distance between at least one of the faces and the cooling area is at least 30 mm.Type: GrantFiled: January 29, 2010Date of Patent: May 26, 2015Assignee: Vestas Wind Systems A/SInventors: Krishnamoorthi Sivalingam, Anand Bahuguni, Ravi Kandasamy, Srikanth Narasimalu, John K. Grevsen, Jesper Nyvad, Paul T. Tietze
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Patent number: 8206112Abstract: A wind turbine having a cooling system, which wind turbine includes a nacelle in connection with which one or more wind turbine components are arranged, is disclosed. The cooling system includes at least one cooling circuit arranged to lead a heat transfer medium to and from one or more of the wind turbine components, at least one cooling device arranged to cool the heat transfer medium, at least one pump arranged in connection with the at least one cooling circuit to circulate the heat transfer medium in the cooling circuit, and at least one medium tank arranged in connection with the cooling circuit. The at least one medium tank is arranged inside the nacelle.Type: GrantFiled: October 28, 2010Date of Patent: June 26, 2012Assignee: Vestas Wind Systems A/SInventors: Poul T. Tietze, Jesper Nyvad, Anand Bahuguni, Ravi Kandasamy, Krishnamoorthi Sivalingam
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Publication number: 20120086215Abstract: The present invention relates to a wind turbine nacelle having a top face with a longitudinal extension in a wind direction, comprising a cooling device extending from the top face of the nacelle and a cover having at least one inner face. The cooling device is enclosed by the top face of the nacelle and the inner face of the cover.Type: ApplicationFiled: January 29, 2010Publication date: April 12, 2012Applicant: VESTAS WIND SYSTEMS A/SInventors: Krishnamoorthi Sivalingam, Anand Bahuguni, Ravi Kandasamy, Srikanth Narasimalu, John K. Grevsen, Jesper Nyvad, Poul T. Tietze
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Publication number: 20120061047Abstract: The present invention relates to a wind turbine nacelle having a top face with a longitudinal extension in a wind direction. The nacelle comprises a cooling device having a cooling area and extending from the first face of the nacelle, and a cover having at least one inner face and at least a front edge facing the wind direction. The cooling device is enclosed by the first face of the nacelle and the inner face of the cover and is arranged in a front distance of at least 440 mm from the front edge of the cover.Type: ApplicationFiled: January 29, 2010Publication date: March 15, 2012Applicant: VESTAS WIND SYSTEMS A/SInventors: Krishnamoorthi Sivalingam, Anand Bahuguni, Ravi Kandasamy, Srikanth Narasimalu, John K. Grevsen, Jesper Nyvad, Paul T. Tietze