Patents by Inventor Bhaskar Nanda MONDAL
Bhaskar Nanda MONDAL 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: 10724435Abstract: A gas turbine engine includes a turbomachine and a fan rotatable by the turbomachine. The fan includes a plurality of fan blades. The gas turbine engine also includes an outer nacelle surrounding the plurality of fan blades and a plurality of part-span inlet guide vanes cantilevered from the outer nacelle at a location forward of the plurality of fan blades along the axial direction. Each of the plurality of inlet guide vanes defines an inner end along the radial direction and it is unconnected with an adjacent part-span inlet guide vane at the inner end.Type: GrantFiled: June 16, 2017Date of Patent: July 28, 2020Assignee: General Electric Co.Inventors: Christopher James Kroger, Brandon Wayne Miller, Trevor Wayne Goerig, David William Crall, Tsuguji Nakano, Jeffrey Donald Clements, Bhaskar Nanda Mondal
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Patent number: 10711797Abstract: A gas turbine engine includes a turbomachine and a fan rotatable by the turbomachine. The fan includes a plurality of fan blades, each of the plurality of fan blades defining a fan blade span along a radial direction. The gas turbine engine further includes an outer nacelle surrounding the plurality of fan blades and a plurality of part-span inlet guide varies attached to the outer nacelle at a location forward of the plurality of fan blades along an axial direction. Each of the plurality of inlet guide vanes defines an IGV span along the radial direction, the IGV span being at least about five percent of the fan blade span and up to about fifty-five percent of the fan blade span.Type: GrantFiled: June 16, 2017Date of Patent: July 14, 2020Assignee: General Electric CompanyInventors: Christopher James Kroger, Brandon Wayne Miller, Trevor Wayne Goerig, David William Crall, Tsuguji Nakano, Jeffrey Donald Clements, Bhaskar Nanda Mondal
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Publication number: 20200200082Abstract: A gear assembly for a turbo machine is provided. The gear assembly includes a first input shaft, a second input shaft, an output shaft, a fixed member, and a spindle. The spindle is extended along a spindle centerline axis. The first input shaft is drivingly connected to the spindle at a first interface. The second input shaft is drivingly connected to the spindle at a second interface. The spindle is connected to the fixed member providing a reactive force at a third interface. The spindle is connected to the output shaft at a fourth interface.Type: ApplicationFiled: December 21, 2018Publication date: June 25, 2020Inventor: Bhaskar Nanda Mondal
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Patent number: 10677260Abstract: A turbine engine that includes a rotor assembly including a plurality of rotor blades, an outer case positioned radially outward from the plurality of rotor blades, and an annular ring coupled to the outer case and positioned between the plurality of rotor blades and the outer case. The annular ring is configured to restrict thermal contraction of the outer case towards the plurality of rotor blades.Type: GrantFiled: February 21, 2017Date of Patent: June 9, 2020Assignee: General Electric CompanyInventors: Veeraraju Vanapalli, Nitesh Jain, Viswanadha Gupta Sakala, Bhaskar Nanda Mondal, Nicholas Joseph Kray
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Publication number: 20200131922Abstract: A passive clearance control limits thermal expansion between stator components relative to rotor components. A control ring controls clearance in a passive manner and is located on or adjacent to stationary components which thermally expand during engine operation. The control ring is formed of material having low coefficient of thermal expansion such as CMCs (Ceramic Matrix Composites) and therefore limits, inhibits or restrains expansion of the adjacent stator components as temperatures increase. Limiting expansion of the stator component reduces rotor/stator clearances and limits parasitic leakage of fluid along the flowpath through the engine core.Type: ApplicationFiled: October 29, 2019Publication date: April 30, 2020Inventors: Bhaskar Nanda MONDAL, John Joseph RAHAIM, Thomas MONIZ, Steven A. ROSS, Joel KIRK, Scott HUNTER, Daniel FUSINATO
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Patent number: 10627167Abstract: A gas turbine engine having a heat absorption device and an associated method are disclosed. The gas turbine engine includes a compressor, a combustor, a turbine, a bleed fluid cavity, and the heat absorption device. The combustor is coupled to the compressor. The turbine is coupled to the compressor and the combustor. The bleed fluid cavity is formed at a first predefined location in the compressor. The heat absorption device is disposed in the bleed fluid cavity and includes a casing, a flow path, and a phase change material. The casing includes an inlet and an outlet. The flow path is within the casing, extends between the inlet and the outlet, and directs an input bleed fluid separated from a fluid stream discharged from the compressor. The phase change material is filled in the casing, separated from the flow path.Type: GrantFiled: September 12, 2017Date of Patent: April 21, 2020Assignee: General Electric CompanyInventors: Karthikeyan Sampath, Atanu Saha, Bhaskar Nanda Mondal, Sanjeev Sai Kumar Manepalli
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Publication number: 20200088037Abstract: An apparatus for a turbine engine comprising an outer casing, an engine core provided within outer casing and having a at least one set of blades, and through which gasses flow in a forward to aft direction, an outer drum located within the outer casing to define an annular cavity. A set of seals extending between the first surface and the second surface to define at least one cooled cavity within the annular cavity.Type: ApplicationFiled: November 6, 2019Publication date: March 19, 2020Inventors: Arnab Sen, Jeffrey Douglas Rambo, Rajesh Kumar, Bhaskar Nanda Mondal, Alan Roy Stuart, Robert Proctor, Christopher Charles Glynn
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Patent number: 10480322Abstract: An apparatus and method for cooling a portion of a turbine engine comprising an outer casing defining an axial centerline, a turbine section through which a flow of combustion gasses flows in a forward to aft direction, an outer drum located between the outer casing and the turbine section defining an annular cavity therebetween. A set of seals extends between the outer casing and outer drum to define at least one cooled cavity.Type: GrantFiled: January 12, 2018Date of Patent: November 19, 2019Assignee: General Electric CompanyInventors: Arnab Sen, Jeffrey Douglas Rambo, Rajesh Kumar, Bhaskar Nanda Mondal, Alan Roy Stuart, Robert Proctor, Christopher Charles Glynn
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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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Patent number: 10393149Abstract: The turbomachine includes a compressor, an inner annular casing, and an outer annular casing. The inner annular casing and the outer annular casing define at least one cavity therebetween. The clearance control system includes a manifold system including at least one conduit disposed within the cavities and configured to channel a flow of cooling fluid between the cavities. The clearance control system also includes an impingement system including a header and at least one plenum configured to channel the flow of cooling fluid to the inner annular casing. The conduits configured to channel the flow of cooling fluid to the impingement system. The clearance control system further includes a channel system including at least one channels configured to channel the flow of cooling fluid to the turbomachine. The channels are configured to control the flow of cooling fluid to the manifold system.Type: GrantFiled: March 2, 2017Date of Patent: August 27, 2019Assignee: General Electric CompanyInventors: Bhaskar Nanda Mondal, Kenneth Edward Seitzer, Monty Lee Shelton, Thomas Ory Moniz, Atanu Saha
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Publication number: 20190257318Abstract: 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: ApplicationFiled: February 21, 2018Publication date: August 22, 2019Inventors: Veeraraju Vanapalli, Bhaskar Nanda Mondal, Jagata Laxmi Narasimharao, Tsuguji Nakano, Subramanian Narayanan
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Publication number: 20190249599Abstract: An aeronautical gas turbine engine includes a turbomachine including a compressor section, a combustion section, a turbine section, and an exhaust section in serial flow order. The aeronautical gas turbine engine additionally includes a closed cycle heat engine including a compressor configured to compress a working fluid; a primary heat exchanger in thermal communication with the turbomachine and the working fluid, the primary heat exchanger configured to transfer heat from the turbomachine to the working fluid; an expander coupled to the compressor for expanding the working fluid; and an output shaft driven by the expander.Type: ApplicationFiled: February 13, 2018Publication date: August 15, 2019Inventors: Arnab Sen, Brandon Wayne Miller, Bhaskar Nanda Mondal, Kishanjit Pal, Daniel Alan Niergarth
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Publication number: 20190218913Abstract: An apparatus and method for cooling a portion of a turbine engine comprising an outer casing defining an axial centerline, a turbine section through which a flow of combustion gasses flows in a forward to aft direction, an outer drum located between the outer casing and the turbine section defining an annular cavity therebetween. A set of seals extends between the outer casing and outer drum to define at least one cooled cavity.Type: ApplicationFiled: January 12, 2018Publication date: July 18, 2019Inventors: Arnab Sen, Jeffrey Douglas Rambo, Rajesh Kumar, Bhaskar Nanda Mondal, Alan Roy Stuart, Robert Proctor, Christopher Charles Glynn
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Publication number: 20190211699Abstract: A turbine engine includes an engine core defining a higher pressure region and a lower pressure region. A seal can fluidly separate the higher pressure region from the lower pressure region and be movably mounted to a component within the turbine engine, where a side of the seal can confront the component.Type: ApplicationFiled: January 9, 2018Publication date: July 11, 2019Inventors: Arnab Sen, Jeffrey Douglas Rambo, Rajesh Kumar, Nathan Evan McCurdy Gibson, Robert Proctor, Bhaskar Nanda Mondal, Steven Douglas Johnson
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Patent number: 10323571Abstract: A method of heating a hollow structure and a heating system are provided. The system includes a plurality of hollow structures spaced circumferentially about an annular flow path. The hollow structures include a heating fluid inlet port, a first plurality of film heating apertures, and a second plurality of film heating apertures. The hollow structures also include a first internal passage extending between the heating fluid inlet port and the first plurality of film heating apertures. The first internal passage includes an impingement leg configured to channel a first flow of heating fluid to a leading edge of the hollow structure. A second internal passage extends between the heating fluid inlet port and the second plurality of film heating apertures through a path along an inner surface of the hollow structure before being channeled to the second plurality of film heating apertures.Type: GrantFiled: December 16, 2015Date of Patent: June 18, 2019Assignee: GENERAL ELECTRIC COMPANYInventors: Sesha Subramanian, Bhaskar Nanda Mondal, Sushilkumar Gulabrao Shevakari, Mayank Krisna Amble
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Patent number: 10316681Abstract: A turbine assembly includes a rotor assembly including a shaft coupled to a plurality of rotor stages including a plurality of turbine blades. The shaft and the plurality of turbine blades define a wheelspace therein. The turbine assembly further includes a plurality of seals in series, at least one seal of the plurality of seals is coupled between a static support member and a respective rotor stage such that a plurality of turbine cavities in series are defined within the wheelspace. Each turbine cavity of the plurality of turbine cavities defined by the plurality of seals receives a pressurized fluid flow that applies an axially aft force to the respective rotor stage of the plurality of rotor stages that at least partially reduces net rotor thrust generated by the rotor assembly during operation, the pressurized fluid flow further provides turbine purge within the wheel space.Type: GrantFiled: May 31, 2016Date of Patent: June 11, 2019Assignee: General Electric CompanyInventors: Jagata Laxmi Narasimharao, Thomas Ory Moniz, Mohamed Musthafa Thoppil, Bhaskar Nanda Mondal, Atanu Saha
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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: 20190085702Abstract: 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 an axial direction and rotatable with one another. The turbomachine also includes a first support member, the first plurality of turbine rotor blades coupled to the spool through the first support member; a second support member, the second plurality of turbine rotor blades supported by the second support member; and a bearing assembly including a first bearing and a second bearing, the first bearing and the second bearing each rotatably supporting the second support member and each being supported by 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
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Publication number: 20190085722Abstract: A turbomachine includes a spool and a turbine section including a turbine rear frame, a turbine, and a support member. The turbine includes a first plurality of turbine rotor blades and a second plurality of turbine rotor blades, the first plurality of turbine rotor blades and second plurality of turbine rotor blades alternatingly spaced along the axial direction and rotatable with one another. The support member extends between the first plurality of turbine rotor blades and the spool and couples the first plurality of turbine rotor blades to the spool. The turbomachine also includes a bearing assembly including a bearing, the bearing rotatably supporting the support member and supported by the turbine rear frame, the bearing spaced apart from the spool along the radial direction.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
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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