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: 20250129741
    Abstract: A turbine engine includes a cooling air duct for cooling air positioned radially between a core air flow path for core air and a bypass airflow passage for bypass air. A heat exchanger is positioned in the cooling air duct to transfer heat from a heat source from within the turbine engine. The heat exchanger may be a condenser. The turbine engine may further include a steam system that extracts water from the combustion gases, vaporizes the water to generate steam, and injects the steam into the core air flow path, the steam system including the condenser to transfer heat from the combustion gases to the cooling air and to condense the water from the combustion gases. The turbine engine may further include a booster fan to increase the pressure of the cooling air and the core air.
    Type: Application
    Filed: January 19, 2024
    Publication date: April 24, 2025
    Inventors: Jeffrey D. Rambo, Bhaskar Nanda Mondal
  • Patent number: 12252992
    Abstract: 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 flow path through the engine core.
    Type: Grant
    Filed: March 4, 2024
    Date of Patent: March 18, 2025
    Assignee: General Electric Company
    Inventors: Bhaskar Nanda Mondal, John Joseph Rahaim, Thomas Moniz, Steven A. Ross, Joel Kirk, Scott Hunter, Daniel Fusinato
  • Patent number: 12247516
    Abstract: A gas turbine engine includes a fan located at a forward portion of the gas turbine engine, and a compressor section and a turbine section arranged in serial flow order. The compressor section and the turbine section together define a core airflow path. A rotary member is rotatable with the fan and with a low pressure turbine of the turbine section. The low pressure turbine includes a rotating drum to which a first airfoil structure is connected and extends radially inward toward the rotary member. A torque frame connects the rotating drum to the rotary member and transfers torque from the first airfoil structure mounted to the rotating drum to the rotary member. The torque frame includes an inner disk mounted to the rotary member, an outer ring and a second airfoil structure formed separately from the outer ring and connected thereto by a releasable connecting structure. The second airfoil structure extends radially inward from the outer ring toward the inner disk.
    Type: Grant
    Filed: September 29, 2022
    Date of Patent: March 11, 2025
    Assignees: General Electric Company, GE Avio S.r.l.
    Inventors: Ranganayakulu Alapati, Peeyush Pankaj, Sanjeev Sai Kumar Manepalli, Bhaskar Nanda Mondal, Thomas Moniz, N V Sai Krishna Emani, Shishir Paresh Shah, Anil Soni, Praveen Sharma, Randy T. Antelo, Antonio Giuseppe D'Ettole
  • Patent number: 12247580
    Abstract: Structures for reducing forward loads in compressors are described. A compressor includes inner and outer circumferential support structures positioned concentrically around a central axis, and an aft-most stage including a vane extending radially inward from the outer circumferential support structure. An axial length of the aft-most stage is defined by a spacer arm of the inner circumferential support structure. The vane includes a root, a tip, and a trailing edge extending between the root and the tip. A ratio of a first radial distance between a first point located at an intersection of the tip of the vane and the trailing edge to a radially inner wall of the spacer arm of the inner circumferential support structure to a second radial distance between the first point and a second point located at an intersection of the root of the vane and the trailing edge is between 0.95 and 4.5.
    Type: Grant
    Filed: May 3, 2023
    Date of Patent: March 11, 2025
    Assignee: General Electric Company
    Inventors: Vaishnav Raghuvaran, Bhaskar Nanda Mondal, Thomas Ory Moniz, Atanu Saha, Vaibhav Deshmukh, Curtis Walton Stover, Andrew Mark Del Donno
  • Patent number: 12241406
    Abstract: A turbine engine for an aircraft including a turbo-engine, a fan having a fan shaft coupled to the turbo-engine, and a steam system. The steam system is fluidly coupled to a core air flow path at a plurality of steam injection locations to selectively inject steam into the core air flow path at each of the plurality of steam injection locations, using a steam flow control valve. The plurality of steam injection locations include (i) an upstream steam injection location located to inject steam into the core air flow path at a primary combustion zone of a combustor or upstream thereof and (ii) a downstream steam injection location located to inject steam into the core air flow path downstream of the primary combustion zone.
    Type: Grant
    Filed: December 13, 2023
    Date of Patent: March 4, 2025
    Assignee: GENEERAL ELECTRIC COMPANY
    Inventors: Rakshit Tirumala, Sushilkumar Shevakari, Arthur W. Sibbach, Jeffrey D. Rambo, Bhaskar Nanda Mondal, Vaibhav M. Deshmukh
  • Patent number: 12221930
    Abstract: A turbomachinery engine includes a fan assembly, a low-pressure turbine, and a gearbox. The fan assembly includes a plurality of fan blades. The low-pressure turbine includes 3-5 rotating stages. The low-pressure turbine includes an area ratio equal to the annular exit area of an aft-most rotating stage of the low-pressure turbine divided by the annular exit area of a forward-most rotating stage of the low-pressure turbine. In some instances, the area ratio is within a range of 3.1-5.1.
    Type: Grant
    Filed: February 1, 2024
    Date of Patent: February 11, 2025
    Assignee: General Electric Company
    Inventors: Pranav R. Kamat, Bhaskar Nanda Mondal, Jeffrey D. Clements
  • Patent number: 12203377
    Abstract: A turbomachine engine includes an engine core including a high-pressure compressor, a high-pressure turbine, and a combustion chamber. The engine core has a length (LCORE), and the high-pressure compressor has an exit stage diameter (DCORE). A power turbine is in flow communication with the high-pressure turbine. A low-pressure shaft is coupled to the power turbine and characterized by a midshaft rating from one hundred fifty (ft/sec)1/2 to three hundred thirty (ft/sec)1/2. The low-pressure shaft has a redline speed between fifty and two hundred fifty feet per second. The turbomachine engine is configured to operate up to the redline speed without passing through a critical speed associated with a first-order bending mode of the low-pressure shaft. A high-pressure shaft is coupled to the high-pressure compressor and the high-pressure turbine and is characterized by a high-speed shaft rating from 1.5 to 6.2, and a ratio of LCORE/DCORE is from 2.1 to 4.3.
    Type: Grant
    Filed: March 24, 2023
    Date of Patent: January 21, 2025
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Bhaskar Nanda Mondal, Narayanan Payyoor, Pranav Kamat
  • Patent number: 12158113
    Abstract: A turbomachinery engine includes a fan assembly, a low-pressure turbine, and a gearbox. The fan assembly includes a plurality of fan blades. The low-pressure turbine includes 3-5 rotating stages. The low-pressure turbine includes an area ratio equal to the annular exit area of an aft-most rotating stage of the low-pressure turbine divided by the annular exit area of a forward-most rotating stage of the low-pressure turbine. In some instances, the area ratio is within a range of 3.1-5.1.
    Type: Grant
    Filed: February 1, 2024
    Date of Patent: December 3, 2024
    Assignee: General Electric Company
    Inventors: Pranav R. Kamat, Bhaskar Nanda Mondal, Jeffrey D. Clements
  • Publication number: 20240392690
    Abstract: A fan assembly for an engine includes a fan disk, fan disk inserts, and fan blades. The fan disk includes disk posts extending in a radial direction from a central region of the fan disk. The disk posts include disk post pressure surfaces that define a first array of dovetail recesses. The fan disk inserts are retained within the first array of dovetail recesses. The fan disk inserts include fan disk insert pressure surfaces that define a second array of dovetail recesses. The fan blades are retained within the second array of dovetail recesses.
    Type: Application
    Filed: May 26, 2023
    Publication date: November 28, 2024
    Applicant: General Electric Company
    Inventors: Vaishnav Raghuvaran, Bhaskar Nanda Mondal, Gary W. Bryant
  • Publication number: 20240392827
    Abstract: A turbomachine engine including an engine core including a high-pressure compressor, which has an exit stage having an exit stage diameter (DCORE), a high-pressure turbine, and a combustion chamber in flow communication with the high-pressure compressor and the high-pressure turbine, a power turbine in flow communication with the high-pressure turbine, and a low-pressure shaft coupled to the power turbine and characterized by a midshaft rating (MSR) between two hundred (ft/sec)1/2 and three hundred (ft/sec)1/2. The low-pressure shaft has a redline speed between fifty and two hundred fifty feet per second (ft/sec). The turbomachine engine is configured to operate up to the redline speed without passing through a critical speed associated with a first-order bending mode of the low-pressure shaft. The low-pressure shaft has a length (LMSR) defined by an engine core length (LCORE) given by: L CORE = [ m ? ( 20 + m ) * n ? ( 10 + n ) ] ( 1 100 ) * D CORE + CIS .
    Type: Application
    Filed: August 7, 2024
    Publication date: November 28, 2024
    Inventors: Narayanan Payyoor, Bhaskar Nanda Mondal
  • Patent number: 12152537
    Abstract: A turbomachinery engine includes a fan assembly, a low-pressure turbine, and a gearbox. The fan assembly includes a plurality of fan blades. The low-pressure turbine includes 3-5 rotating stages. The low-pressure turbine includes an area ratio equal to the annular exit area of an aft-most rotating stage of the low-pressure turbine divided by the annular exit area of a forward-most rotating stage of the low-pressure turbine. In some instances, the area ratio is within a range of 3.1-5.1.
    Type: Grant
    Filed: February 1, 2024
    Date of Patent: November 26, 2024
    Assignee: General Electric Company
    Inventors: Pranav R. Kamat, Bhaskar Nanda Mondal, Jeffrey D. Clements
  • Patent number: 12140082
    Abstract: A turbomachinery engine includes a fan assembly, a low-pressure turbine, and a gearbox. The fan assembly includes a plurality of fan blades. The low-pressure turbine includes 3-5 rotating stages. The low-pressure turbine includes an area ratio equal to the annular exit area of an aft-most rotating stage of the low-pressure turbine divided by the annular exit area of a forward-most rotating stage of the low-pressure turbine. In some instances, the area ratio is within a range of 3.1-5.1.
    Type: Grant
    Filed: May 1, 2024
    Date of Patent: November 12, 2024
    Assignee: General Electric Company
    Inventors: Pranav R. Kamat, Bhaskar Nanda Mondal, Jeffrey D. Clements
  • Publication number: 20240369072
    Abstract: Structures for reducing forward loads in compressors are described. compressor includes inner and outer circumferential support structures positioned concentrically around a central axis, and an aft-most stage including a vane extending radially inward from the outer circumferential support structure. An axial length of the aft-most stage is defined by a spacer arm of the inner circumferential support structure. The vane includes a root, a tip, and a trailing edge extending between the root and the tip. A ratio of a first radial distance between a first point located at an intersection of the tip of the vane and the trailing edge to a radially inner wall of the spacer arm of the inner circumferential support structure to a second radial distance between the first point and a second point located at an intersection of the root of the vane and the trailing edge is between 0.95 and 4.5.
    Type: Application
    Filed: May 3, 2023
    Publication date: November 7, 2024
    Applicant: General Electric Company
    Inventors: Vaishnav Raghuvaran, Bhaskar Nanda Mondal, Thomas Ory Moniz, Atanu Saha, Vaibhav Deshmukh, Curtis Walton Stover, Andrew Mark Del Donno
  • Patent number: 12123358
    Abstract: A turbomachinery engine includes a fan assembly, a low-pressure turbine, and a gearbox. The fan assembly includes a plurality of fan blades. The low-pressure turbine includes 3-5 rotating stages. The low-pressure turbine includes an area ratio equal to the annular exit area of an aft-most rotating stage of the low-pressure turbine divided by the annular exit area of a forward-most rotating stage of the low-pressure turbine. In some instances, the area ratio is within a range of 3.1-5.1.
    Type: Grant
    Filed: April 30, 2024
    Date of Patent: October 22, 2024
    Assignee: General Electric Company
    Inventors: Pranav R. Kamat, Bhaskar Nanda Mondal, Jeffrey D. Clements
  • Patent number: 12123357
    Abstract: A turbomachinery engine includes a fan assembly, a low-pressure turbine, and a gearbox. The fan assembly includes a plurality of fan blades. The low-pressure turbine includes 3-5 rotating stages. The low-pressure turbine includes an area ratio equal to the annular exit area of an aft-most rotating stage of the low-pressure turbine divided by the annular exit area of a forward-most rotating stage of the low-pressure turbine. In some instances, the area ratio is within a range of 3.1-5.1.
    Type: Grant
    Filed: April 29, 2024
    Date of Patent: October 22, 2024
    Assignee: General Electric Company
    Inventors: Pranav R. Kamat, Bhaskar Nanda Mondal, Jeffrey D. Clements
  • Publication number: 20240337228
    Abstract: A turbomachinery engine includes a fan assembly, a low-pressure turbine, and a gearbox. The fan assembly includes a plurality of fan blades. The low-pressure turbine includes four rotating stages. The low-pressure turbine includes an area ratio equal to the annular exit area of an aft-most rotating stage of the low-pressure turbine divided by the annular exit area of a forward-most rotating stage of the low-pressure turbine. In some instances, the area ratio is within a range of 2.0-5.1. Additionally (or alternatively) the low-pressure turbine includes an area-EGT ratio within a range of 1.05-1.6.
    Type: Application
    Filed: June 17, 2024
    Publication date: October 10, 2024
    Applicant: General Electric Company
    Inventors: Pranav R. Kamat, Bhaskar Nanda Mondal, Jeffrey D. Clements
  • Publication number: 20240318614
    Abstract: A turbomachine engine includes an engine core including a high-pressure compressor, a high-pressure turbine, and a combustion chamber in flow communication with the high-pressure compressor and the high-pressure turbine. The engine core has a length (LCORE), and the high-pressure compressor has an exit stage diameter (DCORE). A high-pressure shaft is coupled to the high-pressure compressor and the high-pressure turbine. The high-pressure shaft is characterized by a high-speed shaft rating (HSR) from 1.5 to 6.2, and a ratio of LCORE/DCORE is from 2.1 to 4.3.
    Type: Application
    Filed: June 6, 2023
    Publication date: September 26, 2024
    Inventors: Bhaskar Nanda Mondal, Narayanan Payyoor, Pranav Kamat
  • Publication number: 20240287940
    Abstract: A turbomachinery engine includes a fan assembly, a low-pressure turbine, and a gearbox. The fan assembly includes a plurality of fan blades. The low-pressure turbine includes 3-5 rotating stages. The low-pressure turbine includes an area ratio equal to the annular exit area of an aft-most rotating stage of the low-pressure turbine divided by the annular exit area of a forward-most rotating stage of the low-pressure turbine. In some instances, the area ratio is within a range of 3.1-5.1.
    Type: Application
    Filed: April 30, 2024
    Publication date: August 29, 2024
    Applicant: General Electric Company
    Inventors: Pranav R. Kamat, Bhaskar Nanda Mondal, Jeffrey D. Clements
  • Publication number: 20240287941
    Abstract: A turbomachinery engine includes a fan assembly, a low-pressure turbine, and a gearbox. The fan assembly includes a plurality of fan blades. The low-pressure turbine includes 3-5 rotating stages. The low-pressure turbine includes an area ratio equal to the annular exit area of an aft-most rotating stage of the low-pressure turbine divided by the annular exit area of a forward-most rotating stage of the low-pressure turbine. In some instances, the area ratio is within a range of 3.1-5.1.
    Type: Application
    Filed: May 1, 2024
    Publication date: August 29, 2024
    Applicant: General Electric Company
    Inventors: Pranav R. Kamat, Bhaskar Nanda Mondal, Jeffrey D. Clements
  • Patent number: 12071978
    Abstract: A turbomachine engine including an engine core including a high-pressure compressor, which has an exit stage having an exit stage diameter (DCORE), a high-pressure turbine, and a combustion chamber in flow communication with the high-pressure compressor and the high-pressure turbine, a power turbine in flow communication with the high-pressure turbine, and a low-pressure shaft coupled to the power turbine and characterized by a midshaft rating (MSR) between two hundred (ft/sec)1/2 and three hundred (ft/sec)1/2. The low-pressure shaft has a redline speed between fifty and two hundred fifty feet per second (ft/sec). The turbomachine engine is configured to operate up to the redline speed without passing through a critical speed associated with a first-order bending mode of the low-pressure shaft. The low-pressure shaft has a length (LMSR) defined by an engine core length (LCORE) given by: LCORE=[m(20+m)*n(10+n)](1/100)*DCORE+CIS.
    Type: Grant
    Filed: November 22, 2022
    Date of Patent: August 27, 2024
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Narayanan Payyoor, Bhaskar Nanda Mondal