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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Publication number: 20250129741Abstract: 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: ApplicationFiled: January 19, 2024Publication date: April 24, 2025Inventors: Jeffrey D. Rambo, Bhaskar Nanda Mondal
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Patent number: 12252992Abstract: 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: GrantFiled: March 4, 2024Date of Patent: March 18, 2025Assignee: General Electric CompanyInventors: Bhaskar Nanda Mondal, John Joseph Rahaim, Thomas Moniz, Steven A. Ross, Joel Kirk, Scott Hunter, Daniel Fusinato
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Patent number: 12247516Abstract: 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: GrantFiled: September 29, 2022Date of Patent: March 11, 2025Assignees: 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
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Patent number: 12247580Abstract: 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: GrantFiled: May 3, 2023Date of Patent: March 11, 2025Assignee: General Electric CompanyInventors: Vaishnav Raghuvaran, Bhaskar Nanda Mondal, Thomas Ory Moniz, Atanu Saha, Vaibhav Deshmukh, Curtis Walton Stover, Andrew Mark Del Donno
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Patent number: 12241406Abstract: 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: GrantFiled: December 13, 2023Date of Patent: March 4, 2025Assignee: GENEERAL ELECTRIC COMPANYInventors: Rakshit Tirumala, Sushilkumar Shevakari, Arthur W. Sibbach, Jeffrey D. Rambo, Bhaskar Nanda Mondal, Vaibhav M. Deshmukh
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Patent number: 12221930Abstract: 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: GrantFiled: February 1, 2024Date of Patent: February 11, 2025Assignee: General Electric CompanyInventors: Pranav R. Kamat, Bhaskar Nanda Mondal, Jeffrey D. Clements
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Patent number: 12203377Abstract: 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: GrantFiled: March 24, 2023Date of Patent: January 21, 2025Assignee: GENERAL ELECTRIC COMPANYInventors: Bhaskar Nanda Mondal, Narayanan Payyoor, Pranav Kamat
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Patent number: 12158113Abstract: 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: GrantFiled: February 1, 2024Date of Patent: December 3, 2024Assignee: General Electric CompanyInventors: Pranav R. Kamat, Bhaskar Nanda Mondal, Jeffrey D. Clements
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Publication number: 20240392690Abstract: 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: ApplicationFiled: May 26, 2023Publication date: November 28, 2024Applicant: General Electric CompanyInventors: Vaishnav Raghuvaran, Bhaskar Nanda Mondal, Gary W. Bryant
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Publication number: 20240392827Abstract: 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: ApplicationFiled: August 7, 2024Publication date: November 28, 2024Inventors: Narayanan Payyoor, Bhaskar Nanda Mondal
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Patent number: 12152537Abstract: 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: GrantFiled: February 1, 2024Date of Patent: November 26, 2024Assignee: General Electric CompanyInventors: Pranav R. Kamat, Bhaskar Nanda Mondal, Jeffrey D. Clements
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Patent number: 12140082Abstract: 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: GrantFiled: May 1, 2024Date of Patent: November 12, 2024Assignee: General Electric CompanyInventors: Pranav R. Kamat, Bhaskar Nanda Mondal, Jeffrey D. Clements
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Publication number: 20240369072Abstract: 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: ApplicationFiled: May 3, 2023Publication date: November 7, 2024Applicant: General Electric CompanyInventors: Vaishnav Raghuvaran, Bhaskar Nanda Mondal, Thomas Ory Moniz, Atanu Saha, Vaibhav Deshmukh, Curtis Walton Stover, Andrew Mark Del Donno
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Patent number: 12123358Abstract: 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: GrantFiled: April 30, 2024Date of Patent: October 22, 2024Assignee: General Electric CompanyInventors: Pranav R. Kamat, Bhaskar Nanda Mondal, Jeffrey D. Clements
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Patent number: 12123357Abstract: 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: GrantFiled: April 29, 2024Date of Patent: October 22, 2024Assignee: General Electric CompanyInventors: Pranav R. Kamat, Bhaskar Nanda Mondal, Jeffrey D. Clements
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Publication number: 20240337228Abstract: 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: ApplicationFiled: June 17, 2024Publication date: October 10, 2024Applicant: General Electric CompanyInventors: Pranav R. Kamat, Bhaskar Nanda Mondal, Jeffrey D. Clements
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Publication number: 20240318614Abstract: 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: ApplicationFiled: June 6, 2023Publication date: September 26, 2024Inventors: Bhaskar Nanda Mondal, Narayanan Payyoor, Pranav Kamat
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Publication number: 20240287940Abstract: 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: ApplicationFiled: April 30, 2024Publication date: August 29, 2024Applicant: General Electric CompanyInventors: Pranav R. Kamat, Bhaskar Nanda Mondal, Jeffrey D. Clements
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Publication number: 20240287941Abstract: 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: ApplicationFiled: May 1, 2024Publication date: August 29, 2024Applicant: General Electric CompanyInventors: Pranav R. Kamat, Bhaskar Nanda Mondal, Jeffrey D. Clements
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Patent number: 12071978Abstract: 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: GrantFiled: November 22, 2022Date of Patent: August 27, 2024Assignee: GENERAL ELECTRIC COMPANYInventors: Narayanan Payyoor, Bhaskar Nanda Mondal