Patents by Inventor Hiranya Kumar Nath
Hiranya Kumar Nath 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: 11959643Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a forward liner segment; an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber; and an intermediate member disposed at least partially between the forward and aft liner segments and extending in the circumferential direction.Type: GrantFiled: June 7, 2021Date of Patent: April 16, 2024Assignee: GENERAL ELECTRIC COMPANYInventors: Karthikeyan Sampath, Pradeep Naik, Veeraraju Vanapalli, Perumallu Vukanti, Shai Birmaher, Daniel J. Kirtley, Deepak Ghiya, Rimple Rakeshkumar Rangrej, Saket Singh, Ravindra Shankar Ganiger, Hiranya Kumar Nath, Michael Anthony Benjamin, Rajendra Mahadeorao Wankhade
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Patent number: 11920796Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a forward liner segment; an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber; and an intermediate member disposed at least partially between the forward and aft liner segments and extending in the circumferential direction.Type: GrantFiled: June 7, 2021Date of Patent: March 5, 2024Assignee: GENERAL ELECTRIC COMPANYInventors: Karthikeyan Sampath, Pradeep Naik, Veeraraju Vanapalli, Perumallu Vukanti, Shai Birmaher, Daniel J. Kirtley, Deepak Ghiya, Rimple Rakeshkumar Rangrej, Saket Singh, Ravindra Shankar Ganiger, Hiranya Kumar Nath, Michael Anthony Benjamin, Rajendra Mahadeorao Wankhade
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Publication number: 20240052778Abstract: Variable bleed valves with struts for aerodynamic stability are described. An apparatus described herein includes a variable bleed valve port, and a strut disposed within the variable bleed valve port, the strut defining a plane and a plurality of holes disposed perpendicularly to the plane, the plurality of holes disposed in a pattern to dampen an acoustic response associated with the variable bleed valve port.Type: ApplicationFiled: September 23, 2022Publication date: February 15, 2024Inventors: Nageswar Rao Ganji, Ravindra Shankar Ganiger, Hiranya Kumar Nath, Ambika Shivamurthy, Trevor H. Wood
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Patent number: 11885495Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a liner at least partially defining a combustion chamber of the gas turbine engine, wherein the liner comprises a looped feature.Type: GrantFiled: June 7, 2021Date of Patent: January 30, 2024Assignee: GENERAL ELECTRIC COMPANYInventors: Ravindra Shankar Ganiger, Hiranya Kumar Nath, Daniel J. Kirtley, Shai Birmaher, Pradeep Naik
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Patent number: 11879411Abstract: A gas turbine engine includes a casing, a rotor assembly rotatably mounted within the casing, the rotor assembly comprising a forward rotor portion defining a forward rotor cavity and an aft rotor portion defining an aft rotor cavity, the aft rotor cavity being fluidly isolated from the forward rotor cavity, and a cooling system. The cooling system includes a forward cooling fluid supply, a forward supply line providing fluid communication between the forward cooling fluid supply and the forward rotor cavity, an aft cooling fluid supply, an aft supply line providing fluid communication between the aft cooling fluid supply and the aft rotor cavity, and a flow control system fluidly coupled to the forward supply line and the aft supply line for regulating a flow of forward cooling fluid and a flow of aft cooling fluid.Type: GrantFiled: June 13, 2022Date of Patent: January 23, 2024Assignee: General Electric CompanyInventors: Rajesh Kumar, Prateek Jalan, Kudum Shinde, Atanu Saha, Hiranya Kumar Nath, Ravindra Shankar Ganiger
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Publication number: 20240003543Abstract: A gas turbine engine is provided. The gas turbine engine includes a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order and together defining a working gas flowpath, the turbomachine including an acoustic liner, the acoustic liner having: a flowpath wall exposed to the working gas flowpath, the flowpath wall defining an opening; and a duct wall extending from the flowpath wall defining at least in part an acoustic passage defining a volume, the acoustic passage operable to attenuate noise through the working gas flowpath during an operating condition of the gas turbine engine.Type: ApplicationFiled: June 29, 2022Publication date: January 4, 2024Inventors: Ravikanth Avancha, Ravish Karve, Jeffrey Donald Clements, Hiranya Kumar Nath, Timothy Richard DePuy
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Publication number: 20230417415Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a forward liner segment; an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber; and a fence disposed between the forward and aft liner segments, wherein the fence extends in the circumferential direction, and wherein the fence extends into the combustion chamber along the radial direction.Type: ApplicationFiled: September 11, 2023Publication date: December 28, 2023Inventors: Pradeep Naik, Rimple Rakeshkumar Rangrej, Saket Singh, Narasimha Chiranthan R., Shai Birmaher, Hiranya Kumar Nath, Ravindra Shankar Ganiger
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Patent number: 11846423Abstract: A mixer assembly having a plurality of mixer vanes, each of the plurality of mixer vanes having a first end, a second end, and a body portion extending between the first end and the second end, the body portion having a length, a width, a thickness, a cross-sectional area, a curvature, and a twist, wherein each of the plurality of mixer vanes has a 3-dimensional shape defined by the length, width, thickness, cross-sectional area, curvature, and twist of the body portion, and wherein at least one of the plurality of mixer vanes has a non-uniform 3-dimensional shape.Type: GrantFiled: April 16, 2021Date of Patent: December 19, 2023Assignee: GENERAL ELECTRIC COMPANYInventors: Steven Clayton Vise, Clayton Stuart Cooper, Michael Anthony Benjamin, Hiranya Kumar Nath, Rameshkumar Muthuvel Chandrasekaran
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Patent number: 11835236Abstract: A combustor for a gas turbine engine includes a forward liner segment having an aft end portion. The forward liner segment at least partially defines a primary combustion chamber. The combustor further includes an aft liner segment having a forward end portion. A channel is defined between the forward liner segment and the aft liner segment. The channel directs a stream of dilution air in a counter-flow or reverse direction with respect to combustion gases flowing from the primary combustion chamber during operation of the combustor.Type: GrantFiled: July 5, 2022Date of Patent: December 5, 2023Assignee: General Electric CompanyInventors: Hiranya Kumar Nath, Ravindra Shankar Ganiger, Steven Clayton Vise
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Publication number: 20230358181Abstract: Aero-acoustically damped bleed valves are disclosed. An example variable bleed valve apparatus comprises a variable bleed valve door to actuate the variable bleed valve apparatus, and a variable bleed valve port including an upstream edge and a downstream edge, the VBV port to define a secondary flowpath, the VBV door to cover the VBV port in a closed position, and a vortex device at the upstream edge of the variable bleed valve port, the vortex device including a vorticity generating feature along the upstream edge of the variable bleed valve port.Type: ApplicationFiled: July 17, 2023Publication date: November 9, 2023Inventors: Thomas Malkus, Trevor H. Wood, Giridhar Jothiprasad, Nageswar Ganji, Hiranya Kumar Nath, Ravindra Shankar Ganiger, Ambika Shivamurthy
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Publication number: 20230323835Abstract: A gas turbine engine includes a casing, a rotor assembly rotatably mounted within the casing, the rotor assembly comprising a forward rotor portion defining a forward rotor cavity and an aft rotor portion defining an aft rotor cavity, the aft rotor cavity being fluidly isolated from the forward rotor cavity, and a cooling system. The cooling system includes a forward cooling fluid supply, a forward supply line providing fluid communication between the forward cooling fluid supply and the forward rotor cavity, an aft cooling fluid supply, an aft supply line providing fluid communication between the aft cooling fluid supply and the aft rotor cavity, and a flow control system fluidly coupled to the forward supply line and the aft supply line for regulating a flow of forward cooling fluid and a flow of aft cooling fluid.Type: ApplicationFiled: June 13, 2022Publication date: October 12, 2023Inventors: Rajesh Kumar, Prateek Jalan, Kudum Shinde, Atanu Saha, Hiranya Kumar Nath, Ravindra Shankar Ganiger
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Patent number: 11774098Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a forward liner segment; an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber; and a fence disposed between the forward and aft liner segments, wherein the fence extends in the circumferential direction, and wherein the fence extends into the combustion chamber along the radial direction.Type: GrantFiled: June 7, 2021Date of Patent: October 3, 2023Assignee: GENERAL ELECTRIC COMPANYInventors: Pradeep Naik, Rimple Rakeshkumar Rangrej, Saket Singh, Narasimha Chiranthan R, Shai Birmaher, Hiranya Kumar Nath, Ravindra Shankar Ganiger
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Patent number: 11753965Abstract: Variable bleed valves with inner wall controlled-flow circuits are disclosed. An example apparatus disclosed herein includes a casing segment defining a first flow path, a variable bleed valve port defining a second flow path, and a channel formed in the casing segment, the channel including a first opening into the first flow path, and a second opening into the second flow path, the channel defining a third flow path between the first opening and the second opening.Type: GrantFiled: April 28, 2022Date of Patent: September 12, 2023Assignee: General Electric CompanyInventors: Nageswar Rao Ganji, Ravindra Shankar Ganiger, Hiranya Kumar Nath, Trevor H. Wood, Srinivas Nuthi
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Patent number: 11753942Abstract: An airfoil for gas turbine engines is generally provided. The airfoil defines a span extending between a root and a tip, the airfoil further defines a chord at each point along the span extending between a leading edge and a trailing edge. Further, the airfoil includes at least one frangible airfoil portion, a residual airfoil portion adjacent to the at least one frangible airfoil portion, and one or more zones. The one or more zones may include a plurality of cavities, where at least one or more cavities of the plurality of cavities include inclusions, with the inclusions having one or more materials.Type: GrantFiled: April 11, 2022Date of Patent: September 12, 2023Assignee: General Electric CompanyInventors: Ravindra Shankar Ganiger, Hiranya Kumar Nath, Kirti Arvind Petkar, Viswanadha Gupta Sakala, Nicholas Joseph Kray
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Patent number: 11739698Abstract: Aero-acoustically damped bleed valves are disclosed. An example variable bleed valve apparatus comprises a variable bleed valve door to actuate the variable bleed valve apparatus, and a variable bleed valve port including an upstream edge and a downstream edge, the VBV port to define a secondary flowpath, the VBV door to cover the VBV port in a closed position, and a vortex device at the upstream edge of the variable bleed valve port, the vortex device including a vorticity generating feature along the upstream edge of the variable bleed valve port.Type: GrantFiled: March 1, 2022Date of Patent: August 29, 2023Assignee: GENERAL ELECTRIC COMPANYInventors: Thomas Malkus, Trevor H. Wood, Giridhar Jothiprasad, Nageswar Ganji, Hiranya Kumar Nath, Ravindra Shankar Ganiger, Ambika Shivamurthy
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Patent number: 11725817Abstract: A gas turbine engine and combustor assembly are provided, the combustor assembly including a first liner and a second liner together defining at least in part a combustion chamber, wherein the first liner and the second liner are separated by a gap along the longitudinal direction, and wherein the first liner is forward of the second liner relative to a flow of fluid through the combustion chamber along the longitudinal direction, and wherein the gap is extended along the circumferential direction.Type: GrantFiled: June 30, 2021Date of Patent: August 15, 2023Assignee: General Electric CompanyInventors: Ravindra Shankar Ganiger, Hiranya Kumar Nath, Rajendra Mahadeorao Wankhade, Daniel J. Kirtley, Michael Anthony Benjamin
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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: 20230228220Abstract: Aero-acoustically damped bleed valves are disclosed. An example variable bleed valve apparatus comprises a variable bleed valve door to actuate the variable bleed valve apparatus, and a variable bleed valve port including an upstream edge and a downstream edge, the VBV port to define a secondary flowpath, the VBV door to cover the VBV port in a closed position, and a vortex device at the upstream edge of the variable bleed valve port, the vortex device including a vorticity generating feature along the upstream edge of the variable bleed valve port.Type: ApplicationFiled: March 1, 2022Publication date: July 20, 2023Inventors: Thomas Malkus, Trevor H. Wood, Giridhar Jothiprasad, Nageswar Ganji, Hiranya Kumar Nath, Ravindra Shankar Ganiger, Ambika Shivamurthy
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Publication number: 20230212984Abstract: 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. Varying the geometry of the swirler can provide for improved supply of air, which can improve efficiency and flame control.Type: ApplicationFiled: March 11, 2022Publication date: July 6, 2023Inventors: Steven C. Vise, Pradeep Naik, Perumallu Vukanti, Michael T. Bucaro, Ajoy Patra, R Narasimha Chiranthan, Michael A. Benjamin, Manampathy G. Giridharan, Hiranya Kumar Nath
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Patent number: 11603799Abstract: A combustor for a gas turbine engine includes an inner liner and an outer liner positioned outward of the inner liner along the radial direction such that a combustion chamber is defined between the inner and outer liners. Furthermore, the combustor includes a fuel nozzle configured to supply fuel to the combustion chamber. Moreover, the combustor includes a bristle pack having a base plate and a plurality of bristles extending outward from the base plate such that the bristle pack forms at least a portion of at least one of a heat shield coupled to the fuel nozzle, a deflector of the combustor, or a flare of the combustor.Type: GrantFiled: December 22, 2020Date of Patent: March 14, 2023Assignee: GENERAL ELECTRIC COMPANYInventors: Ravindra Shankar Ganiger, Hiranya Kumar Nath, Michael Anthony Benjamin, Rajendra Mahadeorao Wankhade, Gurunath Gandikota