Patents by Inventor Ajoy Patra
Ajoy Patra 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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Publication number: 20240102653Abstract: A dome-deflector assembly for a gas turbine includes a dome, a deflector, and at least one dome-deflector connecting assembly that includes a connecting member connecting the dome and the deflector together with a cavity being defined between the dome and the deflector. The connecting member extends through the deflector and has a first end arranged at a hot surface side of the deflector and a second end arranged to connect with the dome. The dome-deflector connecting assembly is configured to provide a flow of cooling air from the cavity to the hot surface side of the deflector to cool the first end of the connecting member on the hot surface side of the deflector.Type: ApplicationFiled: December 5, 2023Publication date: March 28, 2024Inventors: Saket Singh, Ravindra Shankar Ganiger, Hiranya Nath, Perumallu Vukanti, Ajoy Patra, Karthikeyan Sampath, Pradeep Naik, Rimple Rangrej, Veera Venkata Amarnath Manem
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Patent number: 11927349Abstract: A deflector assembly for a combustor defining an operational fluid flow. The deflector assembly includes an upstream surface and a downstream surface opposite the upstream surface. One or more fastening mechanisms each extends through the deflector assembly. One or more cooling holes extend through the deflector assembly from the upstream surface to the downstream surface. The one or more cooling holes are located about the one or more fastening mechanisms to operably direct cooling air about the one or more fastening mechanisms at the downstream surface.Type: GrantFiled: July 15, 2022Date of Patent: March 12, 2024Assignee: GENERAL ELECTRIC COMPANYInventors: Vijayaraj Sukumar, Perumallu Vukanti, Pradeep Naik, Ajoy Patra, Karthikeyan Sampath, Rimple Rangrej, Hiranya Nath, Krishnendu Chakraborty, Narasimhan S. Sahana, Saket Singh, Ravindra Shankar Ganiger
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Patent number: 11906165Abstract: An engine can utilize a combustor to combust fuel to drive the engine. A fuel nozzle assembly can supply fuel to the combustor for combustion or ignition of the fuel. The fuel nozzle assembly can include a swirler and a fuel nozzle to supply a mixture of fuel and air for combustion. The fuel nozzle can include both a primary and secondary fuel passage, and an additional air passage to provide for greater flame control, fuel provision, or local fuel and air mixing prior to combustion.Type: GrantFiled: April 11, 2022Date of Patent: February 20, 2024Assignee: General Electric CompanyInventors: Michael T. Bucaro, Ajoy Patra, Pradeep Naik, Perumallu Vukanti, R Narasimha Chiranthan, Clayton S. Cooper, Michael A. Benjamin, Steven C. Vise, Manampathy G. Giridharan, Krishnakumar Venkatesan
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Publication number: 20240053012Abstract: A combustor for a gas turbine engine has an annular inner liner and an annular outer liner forming a combustion chamber therebetween. A dilution horn pair includes dilution horns that provide a flow of an oxidizer gas into the combustion chamber in a dilution zone. At least one of the dilution horns forming the dilution horn pair is arranged so as to provide a lateral flow component of the flow of oxidizer gas therethrough into the combustion chamber, the lateral flow component having a flow direction extending laterally across and non-orthogonal to an axial flow direction of combustion gases within the combustion chamber.Type: ApplicationFiled: October 25, 2023Publication date: February 15, 2024Inventors: Vishal Sanjay Kediya, Pradeep Naik, Ajoy Patra, Narasimhan S. Sahana
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Publication number: 20240044493Abstract: A combustor for a turbomachine engine includes a combustion chamber, a liner forming a boundary of the combustion chamber, and multiple dilution holes through the liner to permit airflow into the combustion chamber. The dilution holes include converging dilution holes and diverging dilution holes, the converging dilution holes having a converging cross-sectional profile and the diverging dilution holes having a diverging cross-sectional profile.Type: ApplicationFiled: October 11, 2023Publication date: February 8, 2024Inventors: Rimple Rangrej, Saket Singh, Pradeep Naik, Ajoy Patra
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Publication number: 20240027066Abstract: An annular combustor includes a combustion liner defining a combustion chamber, the combustion liner having an outer liner and an inner liner and a plurality of dimples in the combustion liner. The combustion liner is characterized by a performance factor greater than or equal to one and less than or equal to seven. An engine includes the annular combustor.Type: ApplicationFiled: December 1, 2022Publication date: January 25, 2024Inventors: Hiranya Nath, Ravindra Shankar Ganiger, Ajoy Patra, Rajendra Wankhade
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Patent number: 11846419Abstract: A dome-deflector assembly for a gas turbine includes a dome, a deflector, and at least one dome-deflector connecting assembly that includes a connecting member connecting the dome and the deflector together with a cavity being defined between the dome and the deflector. The connecting member extends through the deflector and has a first end arranged at a hot surface side of the deflector and a second end arranged to connect with the dome. The dome-deflector connecting assembly is configured to provide a flow of cooling air from the cavity to the hot surface side of the deflector to cool the first end of the connecting member on the hot surface side of the deflector.Type: GrantFiled: July 5, 2022Date of Patent: December 19, 2023Assignee: GENERAL ELECTRIC COMPANYInventors: Saket Singh, Ravindra Shankar Ganiger, Hiranya Nath, Perumallu Vukanti, Ajoy Patra, Karthikeyan Sampath, Pradeep Naik, Rimple Rangrej, Veera Venkata Amarnath Manem
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Patent number: 11828465Abstract: A turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. The combustion section can have a combustor with a combustor liner at least partially defining a combustion chamber, as well as a fuel-air mixer including at least one set of mixing tubes.Type: GrantFiled: March 3, 2022Date of Patent: November 28, 2023Assignee: General Electric CompanyInventors: Pradeep Naik, Manampathy G. Giridharan, Michael T. Bucaro, Ajoy Patra, Perumallu Vukanti, R Narasimha Chiranthan, Gregory A. Boardman
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Publication number: 20230366548Abstract: A combustor for a gas turbine includes a combustor liner, an outer casing surrounding the combustor liner, an ignitor housing extending through an ignitor opening through the liner, and an ignitor disposed within the ignitor housing. The ignitor housing includes a housing wall including at least one airflow inlet passage on a downstream side of the housing wall and arranged within the outer flow passage, and at least one cooling passage on the downstream side within the housing wall. The at least one cooling passage extends along a length of the ignitor housing from the at least one airflow inlet passage and through the inner end of the ignitor housing, the at least one cooling passage being in fluid communication with the at least one airflow inlet passage.Type: ApplicationFiled: August 30, 2022Publication date: November 16, 2023Inventors: Karthikeyan Sampath, Perumallu Vukanti, Ajoy Patra, Pradeep Naik, Hiranya Nath
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Publication number: 20230366551Abstract: An engine can utilize a combustor to combust fuel to drive the engine. A fuel nozzle assembly can supply fuel to the combustor for combustion or ignition of the fuel. The fuel nozzle assembly can include a swirler and a fuel nozzle to supply a mixture of fuel and air for combustion, which can supply a primary fuel supply and a secondary fuel supply. Increasing efficiency and reducing emission require the use of alternative fuels, which combust at higher temperatures or burn at faster burn speeds than traditional fuels, requiring improved fuel introduction without the occurrence of flame holding or flashback.Type: ApplicationFiled: July 11, 2023Publication date: November 16, 2023Inventors: Perumallu Vukanti, Pradeep Naik, Clayton S. Cooper, Michael A. Benjamin, Michael T. Bucaro, Manampathy G. Giridharan, Steven C. Vise, Ajoy Patra, Saket Singh, R Narasimha Chiranthan
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Patent number: 11815269Abstract: A turbine engine that includes an engine core having at least a compressor section and a combustion section. The combustion section includes a combustor. The combustor section or combustor includes a fuel-air mixing assembly fluidly coupled to the compressor section. The fuel-air mixing assembly includes an outer wall, a center body at least partially circumscribed by the outer wall, and an annular flow passage between the outer wall and center body. At least one fuel orifice includes a fuel outlet fluidly coupled to the annular flow passage.Type: GrantFiled: January 27, 2022Date of Patent: November 14, 2023Assignee: General Electric CompanyInventors: Manampathy G. Giridharan, Ajoy Patra, Pradeep Naik, R Narasimha Chiranthan, Perumallu Vukanti, Michael T. Bucaro
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Patent number: 11788726Abstract: A combustor for a turbomachine engine includes a combustion chamber, a liner forming a boundary of the combustion chamber, and multiple dilution holes through the liner to permit airflow into the combustion chamber. The dilution holes include converging dilution holes and diverging dilution holes, the converging dilution holes having a converging cross-sectional profile and the diverging dilution holes having a diverging cross-sectional profile.Type: GrantFiled: March 3, 2022Date of Patent: October 17, 2023Assignee: GENERAL ELECTRIC COMPANYInventors: Rimple Rangrej, Saket Singh, Pradeep Naik, Ajoy Patra
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Publication number: 20230324047Abstract: A deflector assembly for a combustor defining an operational fluid flow. The deflector assembly includes an upstream surface and a downstream surface opposite the upstream surface. One or more fastening mechanisms each extends through the deflector assembly. One or more cooling holes extend through the deflector assembly from the upstream surface to the downstream surface. The one or more cooling holes are located about the one or more fastening mechanisms to operably direct cooling air about the one or more fastening mechanisms at the downstream surface.Type: ApplicationFiled: July 15, 2022Publication date: October 12, 2023Inventors: Vijayaraj Sukumar, Perumallu Vukanti, Pradeep Naik, Ajoy Patra, Karthikeyan Sampath, Rimple Rangrej, Hiranya Nath, Krishnendu Chakraborty, Narasimhan S. Sahana, Saket Singh, Ravindra Shankar Ganiger
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Publication number: 20230304665Abstract: A method of supplying a first fuel and air mixture and a second fuel and air mixture to a combustor. The combustor having a combustion chamber, a dome wall at least partially defining the combustion chamber, at least one fuel cup provided in the dome wall, and at least one ignition tube having an outlet exhausting to the combustion chamber. The method comprising supplying a first flow of compressed air to only the at least one ignition tube, igniting the first fuel and air mixture, supplying the first ignited fuel and air mixture of the combustion chamber, and supplying a second flow of fuel and a second flow of compressed air to the at least one fuel cup.Type: ApplicationFiled: April 18, 2023Publication date: September 28, 2023Inventors: Ajoy Patra, Pradeep Naik, Perumallu Vukanti, Michael T. Bucaro, R Narasimha Chiranthan, Manampathy G. Giridharan, Michael A. Benjamin, Clayton S. Cooper
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Publication number: 20230296250Abstract: A turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. A combustor in the combustion section can include a combustor liner at least partially defining a combustion chamber. The combustor liner can include at least one aperture fluidly coupled to the combustion chamber.Type: ApplicationFiled: May 10, 2022Publication date: September 21, 2023Inventors: Manampathy G. Giridharan, Michael T. Bucaro, Pradeep Naik, Clayton S. Cooper, Michael A. Benjamin, Steven C. Vise, Ajoy Patra, Perumallu Vukanti, R Narasimha Chiranthan
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Publication number: 20230288065Abstract: A dome-deflector assembly for a gas turbine includes a dome, a deflector, and at least one dome-deflector connecting assembly that includes a connecting member connecting the dome and the deflector together with a cavity being defined between the dome and the deflector. The connecting member extends through the deflector and has a first end arranged at a hot surface side of the deflector and a second end arranged to connect with the dome. The dome-deflector connecting assembly is configured to provide a flow of cooling air from the cavity to the hot surface side of the deflector to cool the first end of the connecting member on the hot surface side of the deflector.Type: ApplicationFiled: July 5, 2022Publication date: September 14, 2023Inventors: Saket Singh, Ravindra Shankar Ganiger, Hiranya Nath, Perumallu Vukanti, Ajoy Patra, Karthikeyan Sampath, Pradeep Naik, Rimple Rangrej, Veera Venkata Amarnath Manem
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Publication number: 20230266009Abstract: A turbine engine can include a compressor section, a combustion section, and a turbine section in axial flow arrangement. The combustion section can include a combustor having a fuel-air mixer. The fuel-air mixer can include a body with at least an air passage, as well as a set of mixing passages.Type: ApplicationFiled: May 2, 2022Publication date: August 24, 2023Inventors: Pradeep Naik, Manampathy G. Giridharan, Ajoy Patra, Perumallu Vukanti, R Narasimha Chiranthan
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Patent number: 11725819Abstract: An engine can utilize a combustor to combust fuel to drive the engine. A fuel nozzle assembly can supply fuel to the combustor for combustion or ignition of the fuel. The fuel nozzle assembly can include a swirler and a fuel nozzle to supply a mixture of fuel and air for combustion, which can supply a primary fuel supply and a secondary fuel supply. Increasing efficiency and reducing emission require the use of alternative fuels, which combust at higher temperatures or burn at faster burn speeds than traditional fuels, requiring improved fuel introduction without the occurrence of flame holding or flashback.Type: GrantFiled: February 28, 2022Date of Patent: August 15, 2023Assignee: General Electric CompanyInventors: Perumallu Vukanti, Pradeep Naik, Clayton S. Cooper, Michael A. Benjamin, Michael T. Bucaro, Manampathy G. Giridharan, Steven C. Vise, Ajoy Patra, Saket Singh, R Narasimha Chiranthan
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Publication number: 20230243502Abstract: A turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. The combustion section can include a combustor with a fuel mixer. The fuel mixer can include an outer wall defining a longitudinal direction and having a mixture outlet, a first compressed air flow passage, and a second compressed air flow passage.Type: ApplicationFiled: April 11, 2022Publication date: August 3, 2023Inventors: R Narasimha Chiranthan, Manampathy G. Giridharan, Ajoy Patra, Pradeep Naik, Perumallu Vukanti, Michael T. Bucaro, Hiranya Kumar Nath
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Publication number: 20230235884Abstract: A turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. The combustion section can have a combustor with a combustor liner at least partially defining a combustion chamber, as well as a fuel-air mixer including at least one set of mixing tubes.Type: ApplicationFiled: March 3, 2022Publication date: July 27, 2023Inventors: Pradeep Naik, Manampathy G. Giridharan, Michael T. Bucaro, Ajoy Patra, Perumallu Vukanti, R Narasimha Chiranthan, Gregory A. Boardman