Patents by Inventor Veeraraju VANAPALLI
Veeraraju VANAPALLI 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: 20240026822Abstract: A gas turbine engine having a compressor section, a combustion section, and a turbine section in serial flow arrangement to define a diffuser cavity between the compressor section and the combustor section, and an aft cavity. A compressor discharge pressure duct fluidly draws air from the diffuser cavity, passes it through a heat exchanger to cool the air, and then supplies the cooled air to the aft cavity.Type: ApplicationFiled: July 20, 2022Publication date: January 25, 2024Inventors: Lakshmi Narasimharao Jagata, Prateek Jalan, Veeraraju Vanapalli, Atanu Saha, Scott Alan Schimmels
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Patent number: 11821326Abstract: A turbine containment system is provided. The turbine containment system includes a first containment member surrounding a portion of a turbine including a plurality of rotor disks and rotor blades; and a second containment member in communication with the first containment member, wherein the first containment member and the second containment member together contain each of the rotor disks and the rotor blades therein.Type: GrantFiled: April 27, 2021Date of Patent: November 21, 2023Assignee: General Electric CompanyInventors: Veeraraju Vanapalli, Bhaskar Nanda Mondal, Apostolos Pavlos Karafillis, Kenneth E. Seitzer
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Publication number: 20230336060Abstract: A method and apparatus for forming a rotor for an electric machine includes serially adding layers of material to form a rotor body having a radially-extending post configured to receive a set of electrically-conductive windings, and also having a radially-extending winding end turn support formed contiguously from the rotor body.Type: ApplicationFiled: June 21, 2023Publication date: October 19, 2023Inventors: Veeraraju Vanapalli, Deepak Ghiya, Raghavendra Rao Adharapurapu, Hao Huang, James Patrick Mahle
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Patent number: 11735985Abstract: A method and apparatus for forming a rotor for an electric machine includes serially adding layers of material to form a rotor body having a radially-extending post configured to receive a set of electrically-conductive windings, and also having a radially-extending winding end turn support formed contiguously from the rotor body.Type: GrantFiled: August 7, 2020Date of Patent: August 22, 2023Assignee: GE Aviation Systems LLCInventors: Veeraraju Vanapalli, Deepak Ghiya, Raghavendra Rao Adharapurapu, Hao Huang, James Patrick Mahle
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Publication number: 20230256511Abstract: A method for forming a component includes estimating a dosing plan for powder of a powder bed fusion (PBF) system needed to form the component. The dosing plan includes powder dosing requirements needed per layer to form the component. The method includes providing the dosing plan to a controller of the PBF system. Further, the method includes regulating the powder being supplied to a build chamber of the PBF system from a supply chamber of the PBF system based on the dosing plan. In addition, the method includes additively manufacturing the component via the PBF system using the powder.Type: ApplicationFiled: March 30, 2023Publication date: August 17, 2023Applicant: General Electric CompanyInventors: Johnnattan Tennessee Ugarte, Joanna Mechelle Jayawickrema, Xuefeng Zhang, Jun Zheng Hu, Kishore Vetcha, Veeraraju Vanapalli, Andrew Jean Desrosiers, Ruben Egberto Fairman, Ryan Antony Lozier
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Patent number: 11638959Abstract: A method for forming a component includes estimating a dosing plan for powder of a powder bed fusion (PBF) system needed to form the component. The dosing plan includes powder dosing requirements needed per layer to form the component. The method includes providing the dosing plan to a controller of the PBF system. Further, the method includes regulating the powder being supplied to a build chamber of the PBF system from a supply chamber of the PBF system based on the dosing plan. In addition, the method includes additively manufacturing the component via the PBF system using the powder.Type: GrantFiled: September 3, 2020Date of Patent: May 2, 2023Assignee: General Electric CompanyInventors: Johnnattan Tennessee Ugarte, Joanna Mechelle Jayawickrema, Xuefeng Zhang, Jun Zheng Hu, Kishore Vetcha, Veeraraju Vanapalli, Andrew Jean Desrosiers, Ruben Egberto Fairman, Ryan Antony Lozier
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Patent number: 11566789Abstract: A ferrule in a fuel-air mixer assembly. The ferrule includes a body having (i) a plurality of channels having sidewalls, the plurality of channels leading to a corresponding plurality of exit openings, the plurality of channels configured to guide a first airflow therein and (ii) a plurality of cascade holes formed within the sidewalls of the plurality of channels and defining a plurality of passageways therein that are transverse to the plurality of channels. The ferrule also includes a plurality of airflow modifiers provided within the plurality of channels. The plurality airflow modifiers are configured to reduce a velocity of the first airflow when the first airflow exits through the plurality of exit openings and to generate low velocity vortex pairs to reduce interaction of the first airflow with a second airflow provided through primary vanes located downstream of the plurality of exit openings of the plurality of channels.Type: GrantFiled: March 18, 2022Date of Patent: January 31, 2023Assignee: GENERAL ELECTRIC COMPANYInventors: Saket Singh, Pradeep Naik, Rimple Rangrej, Ranganatha Narasimha Chiranthan, Veeraraju Vanapalli
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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: 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: 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: 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: 20220341345Abstract: A turbine containment system is provided. The turbine containment system includes a first containment member surrounding a portion of a turbine including a plurality of rotor disks and rotor blades; and a second containment member in communication with the first containment member, wherein the first containment member and the second containment member together contain each of the rotor disks and the rotor blades therein.Type: ApplicationFiled: April 27, 2021Publication date: October 27, 2022Inventors: Veeraraju Vanapalli, Bhaskar Nanda Mondal, Apostolos Pavlos Karafillis, Kenneth E. Seitzer
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Publication number: 20220062989Abstract: A method for forming a component includes estimating a dosing plan for powder of a powder bed fusion (PBF) system needed to form the component. The dosing plan includes powder dosing requirements needed per layer to form the component. The method includes providing the dosing plan to a controller of the PBF system. Further, the method includes regulating the powder being supplied to a build chamber of the PBF system from a supply chamber of the PBF system based on the dosing plan. In addition, the method includes additively manufacturing the component via the PBF system using the powder.Type: ApplicationFiled: September 3, 2020Publication date: March 3, 2022Inventors: Johnnattan Tennessee Ugarte, Joanna Mechelle Jayawickrema, Xuefeng Zhang, Jun Zheng Hu, Kishore Vetcha, Veeraraju Vanapalli, Andrew Jean Desrosiers, Ruben Egberto Fairman, Ryan Antony Lozier
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Publication number: 20220045584Abstract: A method and apparatus for forming a rotor for an electric machine includes serially adding layers of material to form a rotor body having a radially-extending post configured to receive a set of electrically-conductive windings, and also having a radially-extending winding end turn support formed contiguously from the rotor body.Type: ApplicationFiled: August 7, 2020Publication date: February 10, 2022Inventors: Veeraraju Vanapalli, Deepak Ghiya, Raghavendra Rao Adharapurapu, Hao Huang, James Patrick Mahle
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Patent number: 11231043Abstract: The present disclosure is directed to a gas turbine engine including a compressor rotor. The compressor rotor includes a first stage compressor airfoil defined at an upstream-most stage of the compressor rotor. The first stage compressor airfoil defines a first stage pressure ratio of at least approximately 1.7 during operation of the gas turbine engine at a tip speed of at least approximately 472 meters per second.Type: GrantFiled: February 21, 2018Date of Patent: January 25, 2022Assignee: General Electric CompanyInventors: Veeraraju Vanapalli, Bhaskar Nanda Mondal, Jagata Laxmi Narasimharao, Tsuguji Nakano, Subramanian Narayanan
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Patent number: 11029029Abstract: A fuel injector heat exchanger assembly is provided, in which the fuel injector assembly includes a body defining an outer surface and an inner surface. The body includes a plurality of walls in concentric arrangement. The plurality of walls defines a plurality of passages including a first passage surrounded by a second passage, and a third passage surrounding the second passage. Each passage is fluidly segregated from one another by the plurality of walls. A first conduit wall is defined through the body from the outer surface. The first conduit wall defines a first conduit in fluid communication with the second passage. The first conduit wall fluidly segregates the first conduit from the third passage. The first conduit is configured to admit a flow of fluid from outside the fuel injector into the second passage.Type: GrantFiled: January 3, 2019Date of Patent: June 8, 2021Assignee: GENERAL ELECTRIC COMPANYInventors: Varun Swaminathan Lakshmanan, Michael Anthony Benjamin, Veeraraju Vanapalli, Karthikeyan Sampath
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Patent number: 10989411Abstract: A turbo machine including a heat exchanger flowpath is generally provided. The turbo machine includes an outer casing extended along an axial direction, a prediffuser defining an inlet passage into a combustion section of the turbo machine, an inner casing extended from the prediffuser, in which a diffuser cavity is defined between the outer casing and the inner casing, a first plenum wall extended outward along a radial direction from the prediffuser, and a second plenum wall extended outward along a radial direction from the prediffuser. The second plenum wall is separated along the axial direction from the first plenum wall. A plenum is defined between the first plenum wall and the second plenum wall. The turbo machine includes a heat exchanger including a first conduit in fluid communication with the diffuser cavity. The first conduit is in fluid communication with a passage, and a second conduit in fluid communication with the passage and the plenum.Type: GrantFiled: January 3, 2019Date of Patent: April 27, 2021Assignee: GENERAL ELECTRIC COMPANYInventors: Karthikeyan Sampath, Varun Swaminathan Lakshmanan, Michael Anthony Benjamin, Veeraraju Vanapalli
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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