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公开(公告)号：US20190218913A1
公开(公告)日：2019-07-18
申请号：US15870313
申请日：2018-01-12
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Arnab Sen , Jeffrey Douglas Rambo , Rajesh Kumar , Bhaskar Nanda Mondal , Alan Roy Stuart , Robert Proctor , Christopher Charles Glynn
Abstract: 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.
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公开(公告)号：US10197007B2
公开(公告)日：2019-02-05
申请号：US14995661
申请日：2016-01-14
Applicant: General Electric Company
Inventor： Durga Srinivas Chillapalli , Hemanth Gudibande Sathyakumar Kumar , Bhaskar Nanda Mondal , Kishanjit Pal , Sushilkumar Gulabrao Shevakari , Thomas Ory Moniz
Abstract: A variable core cowl vent nozzle system is described herein, the system including a core casing at least partially surrounding a core engine of a gas turbine engine, and a core cowl extending aftward from the core casing. The core cowl defines a core cowl vent area between the core cowl and a primary nozzle. At least one of the core cowl and the primary nozzle is movable to vary the core cowl vent area. A method for varying the core cowl vent area by moving one or more of the core cowl and the primary nozzle is also described herein.
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公开(公告)号：US20170204807A1
公开(公告)日：2017-07-20
申请号：US14995661
申请日：2016-01-14
Applicant: General Electric Company
Inventor： Durga Srinivas Chillapalli , Hemanth Gudibande Sathyakumar Kumar , Bhaskar Nanda Mondal , Kishanjit Pal , Sushilkumar Gulabrao Shevakari , Thomas Ory Moniz
CPC classification number: F02K1/06 , F02C7/18 , F02K1/38 , F02K3/06 , F05D2220/36 , F05D2260/205 , F05D2260/608 , Y02T50/675
Abstract: A variable core cowl vent nozzle system is described herein, the system including a core casing at least partially surrounding a core engine of a gas turbine engine, and a core cowl extending aftward from the core casing. The core cowl defines a core cowl vent area between the core cowl and a primary nozzle. At least one of the core cowl and the primary nozzle is movable to vary the core cowl vent area. A method for varying the core cowl vent area by moving one or more of the core cowl and the primary nozzle is also described herein.
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54.发明申请公开(公告)号：US20170175769A1
公开(公告)日：2017-06-22
申请号：US14977098
申请日：2015-12-21
Applicant: General Electric Company
Inventor： Changjie Sun , Yu Xie Mukherjee , Bhaskar Nanda Mondal , Atanu Saha , Marcia Boyle Johnson , Wenfeng Lu
CPC classification number: F01D11/24 , F04D29/164 , F04D29/526 , F04D29/584
Abstract: The turbomachine includes a rotatable member defining an axis of rotation and an inner annular casing extending circumferentially over at least a portion of the rotatable member. The inner annular casing includes a radially outer surface. The turbomachine further includes an outer annular casing extending over at least a portion of the inner annular casing. The inner annular casing and the outer annular casing define a plurality of cavities therebetween. The clearance control system includes a manifold system including a plurality of conduits extending circumferentially about the inner annular casing and disposed within the cavities. The clearance control system also includes an impingement system extending circumferentially about the inner annular casing and disposed within the cavities. The conduits are configured to channel a flow of cooling fluid to the impingement system which is configured to channel the cooling fluid to the radially outer surface of the inner annular casing.
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公开(公告)号：US12247580B2
公开(公告)日：2025-03-11
申请号：US18142745
申请日：2023-05-03
Applicant: General Electric Company
Inventor： Vaishnav Raghuvaran , Bhaskar Nanda Mondal , Thomas Ory Moniz , Atanu Saha , Vaibhav Deshmukh , Curtis Walton Stover , Andrew Mark Del Donno
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.
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Patent Agency Ranking
公开(公告)号：US12241406B1
公开(公告)日：2025-03-04
申请号：US18538037
申请日：2023-12-13
Applicant: General Electric Company
Inventor： Rakshit Tirumala , Sushilkumar Shevakari , Arthur W. Sibbach , Jeffrey D. Rambo , Bhaskar Nanda Mondal , Vaibhav M. Deshmukh
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.
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公开(公告)号：US12158113B2
公开(公告)日：2024-12-03
申请号：US18430283
申请日：2024-02-01
Applicant: General Electric Company
Inventor： Pranav R. Kamat , Bhaskar Nanda Mondal , Jeffrey D. Clements
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.
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公开(公告)号：US20240318614A1
公开(公告)日：2024-09-26
申请号：US18330155
申请日：2023-06-06
Applicant: General Electric Company
Inventor： Bhaskar Nanda Mondal , Narayanan Payyoor , Pranav Kamat
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.
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公开(公告)号：US20240287940A1
公开(公告)日：2024-08-29
申请号：US18651425
申请日：2024-04-30
Applicant: General Electric Company
Inventor： Pranav R. Kamat , Bhaskar Nanda Mondal , Jeffrey D. Clements
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.
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公开(公告)号：US12065254B2
公开(公告)日：2024-08-20
申请号：US18348649
申请日：2023-07-07
Applicant: General Electric Company
Inventor： Narayanan Payyoor , Bhaskar Nanda Mondal , Arda Unsal
CPC classification number: B64D27/10 , F02C3/04 , F02C7/06 , F02C7/36 , F05D2240/60 , F05D2260/40 , F05D2260/96 , F05D2300/211 , F05D2300/2112 , F05D2300/2261 , F05D2300/6033 , F05D2300/614
Abstract: A turbomachine engine including a high-pressure compressor, a high-pressure turbine, a combustion chamber in flow communication with the high-pressure compressor and the high-pressure turbine, and a power turbine in flow communication with the high-pressure turbine. At least one of the high-pressure compressor, the high-pressure turbine, and the power turbine comprises a ceramic matrix composite (CMC) material. The turbomachine engine includes 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 thirty (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.
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