Patents by Inventor Ramana Reddy Kollam
Ramana Reddy Kollam 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: 20240052890Abstract: An air turbine starter (ATS) for starting an engine, having a stator including a housing having an inlet, an outlet, and a flow path extending between the inlet and the outlet and a rotor including a turbine member defining a rotating axis and having a set of blades at least partially disposed within the flow path. The ATS further including a bearing support structure disposed between the rotor and the stator comprising a first bearing support having a first stiffness (K1) and a second bearing support having a second stiffness (K2).Type: ApplicationFiled: December 21, 2022Publication date: February 15, 2024Inventors: Pallavi Tripathi, Subrata Nayak, Ramana Reddy Kollam, Sharad Pundlik Patil, Milind Chandrakant Dhabade, Narendra Dev Mahadevaiah, Ravindra Shankar Ganiger
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Publication number: 20230243270Abstract: An air turbine starter having a housing, a turbine, a drive shaft, and at least one vane. The housing having an inlet, an outlet and a curvilinear flow path extending between the inlet and the outlet. The at last one vane is located within a portion of the curvilinear flow path, and includes an outer wall extending between a root and a tip in a span-wise direction and between a leading edge and a trailing edge in a chord-wise direction. In one aspect, the vane is arranged to define an acute axial angle that is non-constant in the chord-wise or span-wise direction. In another aspect, the vane is arranged to define an acute tangential angle that is non-constant in the chord-wise or span-wise direction.Type: ApplicationFiled: April 11, 2023Publication date: August 3, 2023Inventors: Milind Chandrakant Dhabade, Vishnu Vardhan Venkata Tatiparthi, Ramana Reddy Kollam, Shiloh Montegomery Meyers, Saurya Ranjan Ray, Subrata Nayak
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Patent number: 11634992Abstract: An air turbine starter comprising a housing defining an inlet, an outlet, and a flow path, a turbine having a rotor with circumferentially spaced blades extending into the flow path, a drive shaft operably coupled to and rotating with the rotor, and at least one vane located within the flow path, upstream of the blades. The at least one blade being defined by an acute axial angle and an acute tangential angle.Type: GrantFiled: June 15, 2021Date of Patent: April 25, 2023Assignee: Unison Industries, LLCInventors: Milind Chandrakant Dhabade, Vishnu Vardhan Venkata Tatiparthi, Ramana Reddy Kollam, Shiloh Montegomery Meyers, Saurya Ranjan Ray, Subrata Nayak
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Patent number: 11549376Abstract: A gas turbine engine guide vane heat exchanger has guide vane heat exchanger including electroformed fluid channels in electroformed heat exchanger tubes or a heat exchanger core disposed within airfoil. Non-flammable heat conducting liquid or non-metallic foam may fill space between tubes or core and airfoil. Fluid circuit may include channels within electroformed heat exchanger tubes or the heat exchanger core and extend from inlet manifold to outlet manifold for directing fluid or oil through channels and include fluid or oil supply inlet connected to inlet manifold for receiving the fluid or oil flowed into inlet manifold and a fluid or oil supply outlet connected to fluid or oil supply outlet for discharging fluid or oil flowed out of fluid or oil outlet manifold. Heat exchanger tubes or heat exchanger core, inlet manifold, outlet manifold, supply inlet and supply outlet may be integrally and monolithically electroformed together.Type: GrantFiled: June 30, 2021Date of Patent: January 10, 2023Assignee: General Electric CompanyInventors: Dattu Guru Venkata Jonnalagadda, Sandeep Kumar, Emily Marie Phelps, Merin Sebastian, Gordon Tajiri, Ramana Reddy Kollam
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Patent number: 11408540Abstract: A tube coupling assembly is disclosed, which comprises a first connector for connecting to a tube; a second connector for jointing with the first connector; a first member is adapted to mount on the first connector and operably affixable to the second connector; and a second member is adapted to mount on the second connector, and is capable of being engaged with the first member to prevent separation between the first connector and the second connector.Type: GrantFiled: September 27, 2017Date of Patent: August 9, 2022Assignee: GENERAL ELECTRIC COMPANYInventors: Greedaran Kubendran Jankin, Vinod Shashikant Chaudhari, Dattu G. V. Jonnalagadda, Sandeep Kumar, Rachamadugu Sivaprasad, Ramana Reddy Kollam, Merin Sebastian
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Publication number: 20220243601Abstract: An air turbine starter comprising a housing defining an inlet, an outlet, and a flow path, a turbine having a rotor with circumferentially spaced blades extending into the flow path, a drive shaft operably coupled to and rotating with the rotor, and at least one vane located within the flow path, upstream of the blades. The at least one blade being defined by an acute axial angle and an acute tangential angle.Type: ApplicationFiled: June 15, 2021Publication date: August 4, 2022Inventors: Milind Chandrakant Dhabade, Vishnu Vardhan Venkata Tatiparthi, Ramana Reddy Kollam, Shiloh Montegomery Meyers, Saurya Ranjan Ray, Subrata Nayak
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Publication number: 20220065169Abstract: An air turbine starter having a housing defining an interior with a primary inlet and a primary outlet to define a primary air flow path from the primary inlet to the primary outlet. A nozzle is located within the interior and has circumferentially spaced vanes. A shroud is also located within the interior and circumscribes at least a portion of the vanes. A retention mechanism constrains the axial movement of nozzle.Type: ApplicationFiled: August 10, 2021Publication date: March 3, 2022Inventors: Ramana Reddy Kollam, Parmeet Singh Chhabra, David Raju Yamarthi, David Allan Dranschak, Steven Ryan Kerley, Mark Leslie Rickert
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Publication number: 20210324745Abstract: A gas turbine engine guide vane heat exchanger has guide vane heat exchanger including electroformed fluid channels in electroformed heat exchanger tubes or a heat exchanger core disposed within airfoil. Non-flammable heat conducting liquid or non-metallic foam may fill space between tubes or core and airfoil. Fluid circuit may include channels within electroformed heat exchanger tubes or the heat exchanger core and extend from inlet manifold to outlet manifold for directing fluid or oil through channels and include fluid or oil supply inlet connected to inlet manifold for receiving the fluid or oil flowed into inlet manifold and a fluid or oil supply outlet connected to fluid or oil supply outlet for discharging fluid or oil flowed out of fluid or oil outlet manifold. Heat exchanger tubes or heat exchanger core, inlet manifold, outlet manifold, supply inlet and supply outlet may be integrally and monolithically electroformed together.Type: ApplicationFiled: June 30, 2021Publication date: October 21, 2021Applicant: General Electric CompanyInventors: Dattu Guru Venkata Jonnalagadda, Sandeep Kumar, Emily Marie Phelps, Merin Sebastian, Gordon Tajiri, Ramana Reddy Kollam
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Patent number: 11085309Abstract: The present disclosure is directed to an outer drum rotor assembly for a gas turbine engine including a first outer drum and a second outer drum. Each outer drum defines a radially extended flange adjacent to one another. A plurality of outer drum airfoils is extended inward along the radial direction from between the first outer drum and the second outer drum at the flange.Type: GrantFiled: September 22, 2017Date of Patent: August 10, 2021Assignee: General Electric CompanyInventors: Bhaskar Nanda Mondal, Ramana Reddy Kollam
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Patent number: 11078795Abstract: A gas turbine engine guide vane heat exchanger has guide vane heat exchanger including electroformed fluid channels in electroformed heat exchanger tubes or a heat exchanger core disposed within airfoil. Non-flammable heat conducting liquid or non-metallic foam may fill space between tubes or core and airfoil. Fluid circuit may include channels within electroformed heat exchanger tubes or the heat exchanger core and extend from inlet manifold to outlet manifold for directing fluid or oil through channels and include fluid or oil supply inlet connected to inlet manifold for receiving the fluid or oil flowed into inlet manifold and a fluid or oil supply outlet connected to fluid or oil supply outlet for discharging fluid or oil flowed out of fluid or oil outlet manifold. Heat exchanger tubes or heat exchanger core, inlet manifold, outlet manifold, supply inlet and supply outlet may be integrally and monolithically electroformed together.Type: GrantFiled: November 16, 2017Date of Patent: August 3, 2021Assignee: General Electric CompanyInventors: Dattu Guru Venkata Jonnalagadda, Sandeep Kumar, Emily Marie Phelps, Merin Sebastian, Gordon Tajiri, Ramana Reddy Kollam
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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: 10823001Abstract: A turbomachine includes a spool and a turbine section including a turbine and a turbine center frame. The turbine includes a first plurality of turbine rotor blades and a second plurality of turbine rotor blades alternatingly spaced along the axial direction and rotatable with one another. The turbomachine also includes a bearing assembly substantially completely supporting rotation of the turbine, the bearing assembly including a total of four bearings, each of the four bearings aligned with, or positioned aft of, the turbine center frame.Type: GrantFiled: September 20, 2017Date of Patent: November 3, 2020Assignee: General Electric CompanyInventors: Peeyush Pankaj, Shashank Suresh Puranik, Darek Tomasz Zatorski, Christopher Charles Glynn, Richard Schmidt, Bhaskar Nanda Mondal, Ramana Reddy Kollam
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Patent number: 10654103Abstract: The present disclosure discloses a method of manufacturing a structure with a wall, comprising manufacturing a structure with a wall by using additive manufacturing technology, and dissolving a surface of the wall for reducing thickness of the wall.Type: GrantFiled: September 20, 2018Date of Patent: May 19, 2020Assignees: General Electric Company, Unison Industries, LLCInventors: Dattu G. V. Jonnalagadda, Srinivasan Swaminathan, Yanzhe Yang, Ramana Reddy Kollam, Merin Sebastian, Emily Phelps
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Publication number: 20200094324Abstract: The present disclosure discloses a method of manufacturing a structure with a wall, comprising manufacturing a structure with a wall by using additive manufacturing technology, and dissolving a surface of the wall for reducing thickness of the wall.Type: ApplicationFiled: September 20, 2018Publication date: March 26, 2020Applicant: Unison Industries, LLCInventors: Dattu G.V. Jonnalagadda, Srinivasan Swaminathan, Yanzhe Yang, Ramana Reddy Kollam, Merin Sebastian, Emily Phelps
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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: 20190145264Abstract: A gas turbine engine guide vane heat exchanger has guide vane heat exchanger including electroformed fluid channels in electroformed heat exchanger tubes or a heat exchanger core disposed within airfoil. Non-flammable heat conducting liquid or non-metallic foam may fill space between tubes or core and airfoil. Fluid circuit may include channels within electroformed heat exchanger tubes or the heat exchanger core and extend from inlet manifold to outlet manifold for directing fluid or oil through channels and include fluid or oil supply inlet connected to inlet manifold for receiving the fluid or oil flowed into inlet manifold and a fluid or oil supply outlet connected to fluid or oil supply outlet for discharging fluid or oil flowed out of fluid or oil outlet manifold. Heat exchanger tubes or heat exchanger core, inlet manifold, outlet manifold, supply inlet and supply outlet may be integrally and monolithically electroformed together.Type: ApplicationFiled: November 16, 2017Publication date: May 16, 2019Inventors: Dattu Guru Venkata Jonnalagadda, Sandeep Kumar, Emily Marie Phelps, Merin Sebastian, Gordon Tajiri, Ramana Reddy Kollam
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Publication number: 20190093800Abstract: A tube coupling assembly is disclosed, which comprises a first connector for connecting to a tube; a second connector for jointing with the first connector; a first member is adapted to mount on the first connector and operably affixable to the second connector; and a second member is adapted to mount on the second connector, and is capable of being engaged with the first member to prevent separation between the first connector and the second connector.Type: ApplicationFiled: September 27, 2017Publication date: March 28, 2019Inventors: Greedaran Kubendran Jankin, Vinod Shashikant Chaudhari, Dattu G.V. Jonnalagadda, Sandeep Kumar, Rachamadugu Sivaprasad, Ramana Reddy Kollam, Merin Sebastian
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Publication number: 20190093489Abstract: The present disclosure is directed to an outer drum rotor assembly for a gas turbine engine including a first outer drum and a second outer drum. Each outer drum defines a radially extended flange adjacent to one another. A plurality of outer drum airfoils is extended inward along the radial direction from between the first outer drum and the second outer drum at the flange.Type: ApplicationFiled: September 22, 2017Publication date: March 28, 2019Inventors: Bhaskar Nanda Mondal, Ramana Reddy Kollam
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Publication number: 20190085721Abstract: A turbomachine includes a spool and a turbine section including a turbine and a turbine center frame. The turbine includes a first plurality of turbine rotor blades and a second plurality of turbine rotor blades alternatingly spaced along the axial direction and rotatable with one another. The turbomachine also includes a bearing assembly substantially completely supporting rotation of the turbine, the bearing assembly including a total of four total bearings, each of the four bearings aligned with, or positioned aft of, the turbine center frame.Type: ApplicationFiled: September 20, 2017Publication date: March 21, 2019Inventors: Peeyush Pankaj, Shashank Suresh Puranik, Darek Tomasz Zatorski, Christopher Charles Glynn, Richard Schmidt, Bhaskar Nanda Mondal, Ramana Reddy Kollam