Patents by Inventor Rajendra Mahadeorao WANKHADE
Rajendra Mahadeorao WANKHADE 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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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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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
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Publication number: 20230003382Abstract: 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: ApplicationFiled: June 30, 2021Publication date: January 5, 2023Inventors: Ravindra Shankar Ganiger, Hiranya Kumar Nath, Rajendra Mahadeorao Wankhade, Daniel J. Kirtley, Michael Anthony Benjamin
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Publication number: 20220390115Abstract: 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: ApplicationFiled: June 7, 2021Publication date: December 8, 2022Inventors: 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: 20220390114Abstract: 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; and 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, wherein the forward and aft liner segments are coupled together at a moveable interface.Type: ApplicationFiled: June 7, 2021Publication date: December 8, 2022Inventors: Ravindra Shankar Ganiger, Hiranya Kumar Nath, Daniel J. Kirtley, Shai Birmaher, Veeraraju Vanapalli, Karthikeyan Sampath, Deepak Ghiya, Perumallu Vukanti, Rajendra Mahadeorao Wankhade, Pradeep Naik, Rimple Rakeshkumar Rangrej, Saket Singh
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Publication number: 20220390111Abstract: 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, the liner further defining a gap; and an intermediate member disposed at least partially within the gap of the liner and in fluid communication with the combustion chamber, wherein the intermediate member is retained at a relatively fixed position with respect to the liner by a support extending between the intermediate member and a case of the gas turbine engine.Type: ApplicationFiled: June 7, 2021Publication date: December 8, 2022Inventors: Ravindra Shankar Ganiger, Hiranya Kumar Nath, Daniel J. Kirtley, Shai Birmaher, Veeraraju Vanapalli, Karthikeyan Sampath, Deepak Ghiya, Perumallu Vukanti, Rajendra Mahadeorao Wankhade, Pradeep Naik
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Publication number: 20220390112Abstract: 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, the liner including a dilution slot in fluid communication with the combustion chamber; and one or more guides configured to redirect cooling medium into the dilution slot.Type: ApplicationFiled: June 7, 2021Publication date: December 8, 2022Inventors: Ravindra Shankar Ganiger, Hiranya Kumar Nath, Perumallu Vukanti, Daniel J. Kirtley, Karthikeyan Sampath, Shai Birmaher, Pradeep Naik, Rajendra Mahadeorao Wankhade, Michael Anthony Benjamin, Veeraraju Vanapalli, Deepak Ghiya
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Publication number: 20220195931Abstract: 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: ApplicationFiled: December 22, 2020Publication date: June 23, 2022Inventors: Ravindra Shankar Ganiger, Hiranya Kumar Nath, Michael Anthony Benjamin, Rajendra Mahadeorao Wankhade, Gurunath Gandikota
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Patent number: 10823191Abstract: The present disclosure is directed to a gas turbine engine including a first frame comprising a first bearing assembly, a second frame comprising a second bearing assembly, and a compressor rotor. A first stage compressor airfoil is defined at an upstream-most stage of the compressor rotor. The compressor rotor is rotatable via the first bearing assembly and the second bearing assembly. The first stage compressor airfoil is disposed between the first bearing assembly and the second bearing assembly.Type: GrantFiled: March 15, 2018Date of Patent: November 3, 2020Assignee: General Electric CompanyInventors: Veeraraju Vanapalli, Bhaskar Nanda Mondal, Rajendra Mahadeorao Wankhade, Ramana Reddy Kollam
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Patent number: 10626797Abstract: A compressor for a turbine engine comprises radially spaced inner and outer bands defining a flow path between them, at least one vane extending between the inner and outer bands, a seal adjacent the inner band, and a cooling air circuit through the inner band proximate the seal.Type: GrantFiled: February 15, 2017Date of Patent: April 21, 2020Assignee: General Electric CompanyInventors: Arvind Namadevan, Sivaprakaash Karuppanchetty, Rajesh Kumar, Rajendra Mahadeorao Wankhade
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Publication number: 20190285082Abstract: The present disclosure is directed to a gas turbine engine including a first frame comprising a first bearing assembly, a second frame comprising a second bearing assembly, and a compressor rotor. A first stage compressor airfoil is defined at an upstream-most stage of the compressor rotor. The compressor rotor is rotatable via the first bearing assembly and the second bearing assembly. The first stage compressor airfoil is disposed between the first bearing assembly and the second bearing assembly.Type: ApplicationFiled: March 15, 2018Publication date: September 19, 2019Inventors: Veeraraju Vanapalli, Bhaskar Nanda Mondal, Rajendra Mahadeorao Wankhade, Ramana Reddy Kollam
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Publication number: 20180231026Abstract: A compressor for a turbine engine comprises radially spaced inner and outer bands defining a flow path between them, at least one vane extending between the inner and outer bands, a seal adjacent the inner band, and a cooling air circuit through the inner band proximate the seal.Type: ApplicationFiled: February 15, 2017Publication date: August 16, 2018Inventors: Arvind Namadevan, Sivaprakaash Karuppanchetty, Rajesh Kumar, Rajendra Mahadeorao Wankhade
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Publication number: 20180045074Abstract: An apparatus and method for providing a pressurized air supply to a balance piston assembly to balance an axial load on a gas turbine engine compressor. The pressurized air supply can be supplied by mixing valve mixing a primary and secondary pressure bleed air supply relative to feedback received from the balance piston assembly to maintain a predetermined pressure at the balance piston assembly.Type: ApplicationFiled: February 24, 2017Publication date: February 15, 2018Inventors: Nishant Kumar SINHA, Sanjay RAJU, Rajendra Mahadeorao WANKHADE