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).

  • Publication number: 20220205387
    Abstract: A gas turbine engine having an interdigitated turbine assembly including a first turbine rotor and a second turbine rotor, wherein a total number of stages at the interdigitated turbine assembly is between 3 and 8, and an average stage pressure ratio at the interdigitated turbine assembly is between 1.3 and 1.9. A gear assembly is configured to receive power from the interdigitated turbine assembly, and a fan assembly is configured to receive power from the gear assembly. The interdigitated turbine assembly and the gear assembly are together configured to allow the second turbine rotor to rotate at a second rotational speed greater than a first rotational speed at the first turbine rotor. The fan assembly and the gear assembly are together configured to allow the fan assembly to rotate at a third rotational speed less than the first rotational speed and the second rotational speed.
    Type: Application
    Filed: December 31, 2020
    Publication date: June 30, 2022
    Inventors: Pranav Kamat, Bhaskar Nanda Mondal, Jeffrey Donald Clements, Vaibhav Madhukar Deshmukh
  • Patent number: 11365629
    Abstract: A turbine assembly including a first rotor assembly with a rotatable outer drum from which one or more stages of a plurality of outer drum airfoils is extended radially inward is provided. An outer casing surrounds the outer drum of the first rotor assembly. A seal assembly is coupled to the outer casing and positioned radially outward from an upstream-most stage of the plurality of outer drum airfoils. The seal assembly is positioned in axial alignment with the upstream-most stage of the plurality of outer drum airfoils. The seal assembly separates a first plenum from a second plenum. The second plenum is formed axially aft of the first plenum and is formed by the seal assembly, the outer casing, and the outer drum of the first rotor assembly. The first plenum is positioned radially outward from the upstream-most stage of the plurality of outer drum airfoils.
    Type: Grant
    Filed: April 14, 2021
    Date of Patent: June 21, 2022
    Assignee: General Electric Company
    Inventors: Bhaskar Nanda Mondal, Vinod Shashikant Chaudhari, Rajesh Kumar, Thomas Ory Moniz
  • Patent number: 11280219
    Abstract: A rotor support system for a gas turbine engine includes a rotatable drum rotor and a non-rotatable support casing. The rotor support system includes a bearing assembly configured for positioning between the rotatable drum rotor and the non-rotatable support casing. The bearing assembly includes, at least, a stationary support frame and a rotatable race. Further, the rotatable race is configured to engage the rotatable drum rotor at separate and discrete locations that are circumferentially spaced apart around the rotatable drum rotor.
    Type: Grant
    Filed: November 27, 2019
    Date of Patent: March 22, 2022
    Assignee: General Electric Company
    Inventors: Shashank Suresh Puranik, Bhaskar Nanda Mondal, Richard Schmidt, Peeyush Pankaj, Narayanan Payyoor
  • Patent number: 11280198
    Abstract: 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: Grant
    Filed: November 6, 2019
    Date of Patent: March 22, 2022
    Assignee: General Electric Company
    Inventors: Arnab Sen, Jeffrey Douglas Rambo, Rajesh Kumar, Bhaskar Nanda Mondal, Alan Roy Stuart, Robert Proctor, Christopher Charles Glynn
  • Patent number: 11267577
    Abstract: An aircraft defining a longitudinal centerline and extending between a forward end and an aft end is provided. The aircraft includes a fuselage extending longitudinally between the forward end of the aircraft and the aft end of the aircraft; a primary wing assembly extending laterally outwardly with respect to the longitudinal centerline from a portion of the fuselage; a first engine mounted to the primary wing assembly; and a first engine wing assembly extending outward from the first engine.
    Type: Grant
    Filed: December 6, 2019
    Date of Patent: March 8, 2022
    Assignee: General Electric Company
    Inventors: Bhaskar Nanda Mondal, Arvind Namadevan, Shankar Jayaraman, Keith EJ Blodgett, Arnab Sen
  • Patent number: 11231043
    Abstract: 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: Grant
    Filed: February 21, 2018
    Date of Patent: January 25, 2022
    Assignee: General Electric Company
    Inventors: Veeraraju Vanapalli, Bhaskar Nanda Mondal, Jagata Laxmi Narasimharao, Tsuguji Nakano, Subramanian Narayanan
  • Patent number: 11193720
    Abstract: A gas turbine engine having a heat absorption device and an associated method are disclosed. The gas turbine engine includes a compressor having a compressor discharge nozzle, a combustor coupled to the compressor, a turbine coupled to the combustor and the compressor, a fluid flow passage fluidly coupling the compressor and the turbine and bypassing the combustor, and a heat absorption device disposed fluidly along the fluid flow passage at a first predefined location. The heat absorption device includes a casing having an inlet and an outlet, a flow path within the casing and extending between the inlet and the outlet, wherein the flow path directs an input bleed flow diverted from a fluid stream discharged from the compressor, and a phase change material hermetically sealed within the casing. The phase change material is separated from the flow path.
    Type: Grant
    Filed: March 24, 2020
    Date of Patent: December 7, 2021
    Assignee: General Electric Company
    Inventors: Karthikeyan Sampath, Atanu Saha, Bhaskar Nanda Mondal, Sanjeev Sai Kumar Manepalli
  • Patent number: 11118506
    Abstract: 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: Grant
    Filed: December 21, 2018
    Date of Patent: September 14, 2021
    Assignee: General Electric Company
    Inventor: Bhaskar Nanda Mondal
  • Publication number: 20210262416
    Abstract: A gas turbine engine, the engine including a core turbine engine forming a core flowpath, a rotatable first stage blade assembly in which a bypass airflow passage is formed downstream of the first stage blade assembly, and a shroud positioned at the bypass airflow passage radially outward of the core turbine engine, wherein a first flowpath is formed outward of the shroud at which a first portion of air is flowed, and wherein the shroud and the core turbine engine form a second flowpath therebetween, the core flowpath in fluid communication with the second flowpath to flow a mixture of a second portion of air and combustion gases in the second flowpath.
    Type: Application
    Filed: February 20, 2020
    Publication date: August 26, 2021
    Inventors: Kishanjit Pal, Bhaskar Nanda Mondal, Lajith Vijayan
  • Patent number: 11098592
    Abstract: 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: Grant
    Filed: September 20, 2017
    Date of Patent: August 24, 2021
    Assignee: General Electric Company
    Inventors: Peeyush Pankaj, Shashank Suresh Puranik, Darek Tomasz Zatorski, Christopher Charles Glynn, Richard Schmidt, Bhaskar Nanda Mondal
  • Patent number: 11085309
    Abstract: 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: Grant
    Filed: September 22, 2017
    Date of Patent: August 10, 2021
    Assignee: General Electric Company
    Inventors: Bhaskar Nanda Mondal, Ramana Reddy Kollam
  • Publication number: 20210171211
    Abstract: An aircraft defining a longitudinal centerline and extending between a forward end and an aft end is provided. The aircraft includes a fuselage extending longitudinally between the forward end of the aircraft and the aft end of the aircraft; a primary wing assembly extending laterally outwardly with respect to the longitudinal centerline from a portion of the fuselage; a first engine mounted to the primary wing assembly; and a first engine wing assembly extending outward from the first engine.
    Type: Application
    Filed: December 6, 2019
    Publication date: June 10, 2021
    Inventors: Bhaskar Nanda Mondal, Arvind Namadevan, Shankar Jayaraman, Keith EJ Blodgett, Arnab Sen
  • Publication number: 20210156279
    Abstract: A rotor support system for a gas turbine engine includes a rotatable drum rotor and a non-rotatable support casing. The rotor support system includes a bearing assembly configured for positioning between the rotatable drum rotor and the non-rotatable support casing. The bearing assembly includes, at least, a stationary support frame and a rotatable race. Further, the rotatable race is configured to engage the rotatable drum rotor at separate and discrete locations that are circumferentially spaced apart around the rotatable drum rotor.
    Type: Application
    Filed: November 27, 2019
    Publication date: May 27, 2021
    Inventors: Shashank Suresh Puranik, Bhaskar Nanda Mondal, Richard Schmidt, Peeyush Pankaj, Narayanan Payyoor
  • Patent number: 10941706
    Abstract: 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: Grant
    Filed: February 13, 2018
    Date of Patent: March 9, 2021
    Assignee: General Electric Company
    Inventors: Arnab Sen, Brandon Wayne Miller, Bhaskar Nanda Mondal, Kishanjit Pal, Daniel Alan Niergarth
  • Patent number: 10914194
    Abstract: 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: Grant
    Filed: September 20, 2017
    Date of Patent: February 9, 2021
    Assignee: General Electric Company
    Inventors: Peeyush Pankaj, Shashank Suresh Puranik, Darek Tomasz Zatorski, Christopher Charles Glynn, Richard Schmidt, Bhaskar Nanda Mondal
  • Patent number: 10823001
    Abstract: 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: Grant
    Filed: September 20, 2017
    Date of Patent: November 3, 2020
    Assignee: General Electric Company
    Inventors: Peeyush Pankaj, Shashank Suresh Puranik, Darek Tomasz Zatorski, Christopher Charles Glynn, Richard Schmidt, Bhaskar Nanda Mondal, Ramana Reddy Kollam
  • Patent number: 10823191
    Abstract: 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: Grant
    Filed: March 15, 2018
    Date of Patent: November 3, 2020
    Assignee: General Electric Company
    Inventors: Veeraraju Vanapalli, Bhaskar Nanda Mondal, Rajendra Mahadeorao Wankhade, Ramana Reddy Kollam
  • Patent number: 10815886
    Abstract: A gas turbine engine includes a compressor section and a turbine section. The turbine section includes a drive turbine and is located downstream of the compressor section. The gas turbine engine also includes a fan mechanically coupled to and rotatable with the drive turbine such that the fan is rotatable by the drive turbine at the same rotational speed as the drive turbine, the fan defining a fan pressure ratio and including a plurality of fan blades, each fan blade defining a fan tip speed. During operation of the gas turbine engine at a rated speed, the fan pressure ratio of the fan is less than 1.5 and the fan tip speed of each of the fan blades is greater than 1,250 feet per second.
    Type: Grant
    Filed: June 16, 2017
    Date of Patent: October 27, 2020
    Assignee: General Electric Company
    Inventors: Christopher James Kroger, Brandon Wayne Miller, Trevor Wayne Goerig, David William Crall, Tsuguji Nakano, Jeffrey Donald Clements, Bhaskar Nanda Mondal
  • Patent number: 10781709
    Abstract: 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: Grant
    Filed: January 9, 2018
    Date of Patent: September 22, 2020
    Assignee: General Electric Company
    Inventors: Arnab Sen, Jeffrey Douglas Rambo, Rajesh Kumar, Nathan Evan McCurdy Gibson, Robert Proctor, Bhaskar Nanda Mondal, Steven Douglas Johnson
  • Publication number: 20200240720
    Abstract: A gas turbine engine having a heat absorption device and an associated method are disclosed. The gas turbine engine includes a compressor having a compressor discharge nozzle, a combustor coupled to the compressor, a turbine coupled to the combustor and the compressor, a fluid flow passage fluidly coupling the compressor and the turbine and bypassing the combustor, and a heat absorption device disposed fluidly along the fluid flow passage at a first predefined location. The heat absorption device includes a casing having an inlet and an outlet, a flow path within the casing and extending between the inlet and the outlet, wherein the flow path directs an input bleed flow diverted from a fluid stream discharged from the compressor, and a phase change material hermetically sealed within the casing. The phase change material is separated from the flow path.
    Type: Application
    Filed: March 24, 2020
    Publication date: July 30, 2020
    Inventors: Karthikeyans Sampath, Atanu Saha, Bhaskar Nanda Mondal, Sanjeev Sai Kumar Manepalli