Patents by Inventor Rimple Rangrej
Rimple Rangrej 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: 20240133552Abstract: In one aspect, a combustor for a turbomachine engine includes a combustion chamber and a component in operable flow with the combustion chamber. The component has a porous structure that defines multiple channels, that are adapted to configure the component as a damper to reduce combustion dynamics of the combustor. In another aspect, a combustor of a turbomachine engine includes a diffuser, a combustor component positioned aft of the diffuser to receive cooling air therefrom, and a support structure in operable flow with the diffuser and the combustor component and positioned therebetween. The support structure has a porous structure that defines multiple channels, which are adapted to improve a backflow margin of the cooling air by reducing turbulence of the cooling air.Type: ApplicationFiled: May 8, 2023Publication date: April 25, 2024Inventors: Karthikeyan Sampath, Rimple Rangrej, Pradeep Naik, Saket Singh, Deepak Ghiya, Perumallu Vukanti
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Patent number: 11965653Abstract: A combustor for a gas turbine engine has a combustor liner that has a cold surface side and a hot surface side, the liner defining an upstream end and a downstream end, and a dilution opening through the combustor liner. The dilution opening includes a main dilution hole portion having an upstream edge and a downstream edge, a notched portion disposed at the upstream edge and extending upstream from the upstream edge, the notched portion being in fluid communication with the main dilution hole portion, and a slotted portion disposed at the downstream edge and extending downstream of the downstream edge, the slotted portion being in fluid communication with the main dilution hole portion.Type: GrantFiled: June 23, 2021Date of Patent: April 23, 2024Assignee: GENERAL ELECTRIC COMPANYInventors: Ranganatha Narasimha Chiranthan, Rimple Rangrej, Saket Singh, Pradeep Naik, Gregory A. Boardman
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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: 11920790Abstract: A combustor liner for a combustor of a gas turbine includes an outer liner having a plurality of outer liner segments, and an inner liner having a plurality of inner liner segments. Each segment of the inner liner and the outer liner includes at least one slotted dilution opening therethrough extending in a circumferential direction, and each slotted dilution opening includes a deflector wall extending radially from the respective liner into a dilution zone of a combustion chamber between the outer liner and the inner liner. The at least one slotted dilution opening may be a curved slot (either concave or convex) dilution opening, and the curved slot dilution openings for each segment of the outer liner and the inner liner may be connected so as to provide a wavy slotted dilution opening extending annularly through the outer liner and the inner liner.Type: GrantFiled: January 28, 2022Date of Patent: March 5, 2024Assignee: GENERAL ELECTRIC COMPANYInventors: Saket Singh, Pradeep Naik, Rimple Rangrej, Ranganatha Narasimha Chiranthan, Krishnendu Chakraborty, Shai Birmaher
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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: 20230408093Abstract: A swirler assembly for a combustor includes at least one swirler including a plurality of swirl vanes arrayed about an axis of the swirler. The plurality of swirl vanes includes a first ring of first sub-vanes and a second ring of second sub-vanes, the first ring of first sub-vanes and the second ring of second sub-vanes being separated by a gap therebetween.Type: ApplicationFiled: September 1, 2023Publication date: December 21, 2023Inventors: Gurunath Gandikota, Karthikeyan Sampath, Perumallu Vukanti, Allen M. Danis, Scott M. Bush, Steven Clayton Vise, Hari Ravi Chandra, Rimple Rangrej, Saket Singh, Pradeep Naik, Neeraj Kumar Mishra, Arvind Kumar Rao, Balasubramaniam Venkatanarayanan, Ranjeet Kumar Mishra
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Publication number: 20230408098Abstract: A combustor for a gas turbine includes a combustor liner having an outer liner and an inner liner defining a combustion chamber therebetween. At least one of the outer liner and the inner liner includes a dilution fence arranged in a dilution zone of the combustion chamber. The dilution fence extends into the combustion chamber and has at least one secondary fuel nozzle opening therethrough, and at least one secondary fuel nozzle is arranged through the at least one secondary fuel nozzle opening.Type: ApplicationFiled: May 25, 2022Publication date: December 21, 2023Inventors: Saket Singh, Rimple Rangrej, Pradeep Naik, Michael A. Benjamin, Joseph Zelina
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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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Publication number: 20230383949Abstract: A combustor for a gas turbine has a combustor liner including an upstream liner portion, and a downstream liner portion. The upstream liner portion includes an outer shell and a heat shield panel, with a baffle cavity therebetween. The outer shell includes an outer shell cooling opening for providing a flow of compressed air to the baffle cavity, and the heat shield panel includes a heat shield panel cooling opening at a downstream end of the heat shield panel. A fence is arranged at a downstream side of the heat shield panel cooling opening and extends beyond a hot side surface of the heat shield panel into a combustion chamber. The heat shield panel cooling opening provides a flow of the compressed air therethrough from the baffle cavity for cooling of the heat shield panel and for providing at least partial dilution of combustion gases within the combustion chamber.Type: ApplicationFiled: September 16, 2022Publication date: November 30, 2023Inventors: Perumallu Vukanti, Karthikeyan Sampath, Pradeep Naik, Ranganatha Narasimha Chiranthan, Rimple Rangrej, Hiranya Nath, Ravindra Shankar Ganiger
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Patent number: 11815267Abstract: A combustor liner for a gas turbine has a cold side liner segment, and a hot side liner segment, with a baffle cavity between the cold side liner segment and the hot side liner segment. At least one cooling airflow dispersing member is arranged within the baffle cavity. The at least one cooling airflow dispersing member includes a main cavity portion, and at least one peripheral cavity portion surrounding the main cavity portion. The main cavity portion includes a main cavity inlet side having a cooling airflow opening, a main cavity outlet side having plurality of hot side cooling airflow openings, and at least one peripheral cavity outlet flow passage providing fluid communication between the main cavity portion and the at least one peripheral cavity portion. The at least one peripheral cavity portion includes a peripheral cavity outlet side having a plurality of hot side cooling airflow openings.Type: GrantFiled: June 28, 2022Date of Patent: November 14, 2023Assignee: GENERAL ELECTRIC COMPANYInventors: Ranganatha Narasimha Chiranthan, Karthikeyan Sampath, Perumallu Vukanti, Rimple Rangrej, Ravindra Shankar Ganiger, Hiranya Nath
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Publication number: 20230358403Abstract: A combustor for a gas turbine engine. The combustor has a combustor liner that includes a vortex turbulence generator. The vortex turbulence generator has a flow passage extending therethrough, the flow passage being defined by a wall about a periphery of the flow passage, and a plurality of vortex generating turbulators disposed on the wall, each of the plurality of vortex generating turbulators a projection portion extending from a surface of the wall into the flow passage and generating a vortex turbulent flow of an oxidizer passing through the flow passage from a cold surface side of the combustor liner to a hot surface side of the combustor liner.Type: ApplicationFiled: July 18, 2023Publication date: November 9, 2023Inventors: Saket Singh, Pradeep Nalk, Daniel J. Kirtley, Rimple Rangrej, Ranganatha Narasimha Chiranthan
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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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Patent number: 11761632Abstract: A dome assembly for a combustor includes: at least one swirler assembly including: at least one swirler including a plurality of swirl vanes arrayed about an axis, the plurality of swirl vanes oriented so as to impart a tangential velocity to air passing through the swirler parallel to the axis; each of the plurality of swirl vanes having a thickness and including a plurality of edges which collectively define a peripheral boundary of the respective swirl vane; wherein at least a selected one of the plurality of swirl vanes includes at least one void passing through the thickness of the selected swirl vane, the void disposed within the peripheral boundary of the selected swirl vane.Type: GrantFiled: August 5, 2021Date of Patent: September 19, 2023Assignee: GENERAL ELECTRIC COMPANYInventors: Gurunath Gandikota, Karthikeyan Sampath, Perumallu Vukanti, Allen M. Danis, Scott M. Bush, Steven Clayton Vise, Hari Ravi Chandra, Rimple Rangrej, Saket Singh, Pradeep Naik, Neeraj Kumar Mishra, Arvind Kumar Rao, Balasubramaniam Venkatanarayanan, Ranjeet Kumar Mishra
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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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Patent number: 11747019Abstract: A combustor liner has an annular outer liner and an annular inner liner that define a combustion chamber therebetween, the combustion chamber having a dilution zone. The annular outer liner and the annular inner liner each has a converging-diverging section extending into the dilution zone of the combustion chamber that form a throat between them. Each of the converging-diverging sections includes at least one dilution opening defined through the respective converging-diverging section at the throat for providing a flow of an oxidizer through a respective liner to the dilution zone of the combustion chamber.Type: GrantFiled: September 2, 2022Date of Patent: September 5, 2023Assignee: GENERAL ELECTRIC COMPANYInventors: Hiranya Nath, Ravindra Shankar Ganiger, Michael A. Benjamin, Steven C. Vise, Perumallu Vukanti, Sripathi Mohan, Rimple Rangrej
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Publication number: 20230266007Abstract: A combustor liner for a gas turbine has a cold side liner segment, and a hot side liner segment, with a baffle cavity between the cold side liner segment and the hot side liner segment. At least one cooling airflow dispersing member is arranged within the baffle cavity. The at least one cooling airflow dispersing member includes a main cavity portion, and at least one peripheral cavity portion surrounding the main cavity portion. The main cavity portion includes a main cavity inlet side having a cooling airflow opening, a main cavity outlet side having plurality of hot side cooling airflow openings, and at least one peripheral cavity outlet flow passage providing fluid communication between the main cavity portion and the at least one peripheral cavity portion. The at least one peripheral cavity portion includes a peripheral cavity outlet side having a plurality of hot side cooling airflow openings.Type: ApplicationFiled: June 28, 2022Publication date: August 24, 2023Inventors: Ranganatha Narasimha Chiranthan, Karthikeyan Sampath, Perumallu Vukanti, Rimple Rangrej, Ravindra Shankar Ganiger, Hiranya Nath
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Patent number: 11703225Abstract: A combustor liner for a combustor of a gas turbine includes an outer liner extending circumferentially about a combustor centerline, and an inner liner extending circumferentially about the combustor centerline, where the outer liner and the inner liner define a combustion chamber therebetween. At least one of the outer liner and the inner liner includes a dilution flow assembly comprising, (a) an annular slot dilution opening, and (b) a dilution fence extending between an upstream side of the annular slot dilution opening to a downstream side of the annular slot dilution opening, and extending into the combustion chamber, the dilution fence including a plurality of dilution openings therethrough for providing a flow of an oxidizer through the dilution fence into the combustion chamber.Type: GrantFiled: May 13, 2022Date of Patent: July 18, 2023Assignee: GENERAL ELECTRIC COMPANYInventors: Saket Singh, Pradeep Naik, Rimple Rangrej, Shai Birmaher, Ranganatha Narasimha Chiranthan, Ajoy Patra, Ravindra Shankar Ganiger, Hiranya Nath
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Publication number: 20230194087Abstract: A combustor liner for a combustor of a gas turbine includes an outer liner extending circumferentially about a combustor centerline, and an inner liner extending circumferentially about the combustor centerline, where the outer liner and the inner liner define a combustion chamber therebetween. At least one of the outer liner and the inner liner includes a dilution flow assembly comprising, (a) an annular slot dilution opening, and (b) a dilution fence extending between an upstream side of the annular slot dilution opening to a downstream side of the annular slot dilution opening, and extending into the combustion chamber, the dilution fence including a plurality of dilution openings therethrough for providing a flow of an oxidizer through the dilution fence into the combustion chamber.Type: ApplicationFiled: May 13, 2022Publication date: June 22, 2023Inventors: Saket Singh, Pradeep Naik, Rimple Rangrej, Shai Birmaher, Ranganatha Narasimha Chiranthan, Ajoy Patra, Ravindra Shankar Ganiger, Hiranya Nath