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公开(公告)号：US11624290B2
公开(公告)日：2023-04-11
申请号：US17143115
申请日：2021-01-06
Applicant: General Electric Company
Inventor： Nathan Evan McCurdy Gibson , Christopher Jon Potokar , Hariharan Manickavasagam Sarojini , Arnab Sen , Bikramjit Chatterjee
IPC: F01D11/02
Abstract: An aspirating face seal between high and low pressure regions of a turbomachine at a juncture between rotatable and non-rotatable members of turbomachine includes gas bearing rotatable and non-rotatable face surfaces. Primary and starter seal teeth and optional deflector seal tooth are mounted on seal teeth carrier on rotatable member. Non-rotatable face surface is mounted on an annular slider on the non-rotatable member. A pull-off biasing means urges the annular slider away from the rotatable member and the non-rotatable face surface away from the rotatable surface. A secondary seal is in sealing engagement with the annular slider in the low pressure region and the pull-off biasing means is located radially outwardly of the annular slider in the high pressure region. Biasing means may include coil springs within spring chambers of circumferentially spaced cartridges. Tongues extend inwardly from spring chambers into grooves in slider.
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公开(公告)号：US11280198B2
公开(公告)日：2022-03-22
申请号：US16675918
申请日：2019-11-06
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Arnab Sen , Jeffrey Douglas Rambo , Rajesh Kumar , Bhaskar Nanda Mondal , Alan Roy Stuart , Robert Proctor , Christopher Charles Glynn
IPC: F01D5/24 , F01D5/08 , F01D1/24 , F02K3/072 , F01D11/00 , F02C7/18 , F01D25/14 , F02C7/12 , F01D1/26
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.
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公开(公告)号：US11267577B2
公开(公告)日：2022-03-08
申请号：US16705384
申请日：2019-12-06
Applicant: General Electric Company
Inventor： Bhaskar Nanda Mondal , Arvind Namadevan , Shankar Jayaraman , Keith EJ Blodgett , Arnab Sen
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.
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公开(公告)号：US10480322B2
公开(公告)日：2019-11-19
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：US20190211699A1
公开(公告)日：2019-07-11
申请号：US15865359
申请日：2018-01-09
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Arnab Sen , Jeffrey Douglas Rambo , Rajesh Kumar , Nathan Evan McCurdy Gibson , Robert Proctor , Bhaskar Nanda Mondal , Steven Douglas Johnson
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.
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Patent Agency Ranking
公开(公告)号：US11293375B2
公开(公告)日：2022-04-05
申请号：US16788384
申请日：2020-02-12
Applicant: General Electric Company
Inventor： Arvind Namadevan , Hari Shanker Thakur , Jeffrey Douglas Rambo , Arnab Sen , Siddhartha Pal
Abstract: An ejector assembly includes a primary nozzle in fluid communication with a primary fluid inlet, a secondary nozzle in fluid communication with a secondary fluid inlet, the primary nozzle being oriented concentrically within the secondary nozzle and the secondary nozzle having a venturi downstream of the primary nozzle, and the primary nozzle having a variable cross-sectional area. A gas turbine engine includes a source of high pressure air, a region of low pressure air, and an ejector assembly, the ejector assembly includes a primary nozzle in fluid communication with a primary fluid inlet, the primary fluid inlet in fluid communication with the source of high pressure air, a secondary nozzle in fluid communication with a secondary fluid inlet, the secondary fluid inlet in fluid communication with the region of low pressure air, the primary nozzle being oriented concentrically within the secondary nozzle and the secondary nozzle having a venturi downstream of the primary nozzle, and the primary nozzle having a variable cross-sectional area.
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公开(公告)号：US11143104B2
公开(公告)日：2021-10-12
申请号：US15899831
申请日：2018-02-20
Applicant: General Electric Company
Inventor： Kishanjit Pal , Arnab Sen , Pranav R. Kamat , Brandon Wayne Miller , Daniel Alan Niergarth
Abstract: A method of operating a thermal management system for a gas turbine engine includes determining the gas turbine engine is in a first operating mode; transferring heat from a first heat source exchanger to a heat sink system in response to determining the gas turbine engine is in the first operation mode, the first heat source exchanger thermally coupled to a first system/component of the gas turbine engine; determining the gas turbine engine is in a second operating mode, the second operating mode being different than the first operating mode; and transferring heat from a second heat source exchanger to the heat sink system in response to determining the gas turbine engine is in the second operation mode, the second heat source exchanger thermally coupled to a second system/component of the gas turbine engine, the second system/component being different than the first system/component.
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公开(公告)号：US11092024B2
公开(公告)日：2021-08-17
申请号：US16155107
申请日：2018-10-09
Applicant: General Electric Company
Inventor： Arvind Namadevan , Weize Kang , Hari Shankar Thakur , Arnab Sen , Mayur Ghawat
Abstract: The present disclosure is directed to a system for mitigating rotor bow at a turbine engine. The system includes a casing circumferentially surrounding a rotor assembly in which a heat pipe is attached to the casing and extended circumferentially around the rotor assembly.
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公开(公告)号：US20210171211A1
公开(公告)日：2021-06-10
申请号：US16705384
申请日：2019-12-06
Applicant: General Electric Company
Inventor： Bhaskar Nanda Mondal , Arvind Namadevan , Shankar Jayaraman , Keith EJ Blodgett , Arnab Sen
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.
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公开(公告)号：US10900369B2
公开(公告)日：2021-01-26
申请号：US16129218
申请日：2018-09-12
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nathan Evan McCurdy Gibson , Christopher Jon Potokar , Hariharan Manickavasagam Sarojini , Arnab Sen , Bikramjit Chatterjee
IPC: F01D11/02
Abstract: An aspirating face seal between high and low pressure regions of a turbomachine at a juncture between rotatable and non-rotatable members of turbomachine includes gas bearing rotatable and non-rotatable face surfaces. Primary and starter seal teeth and optional deflector seal tooth are mounted on seal teeth carrier on rotatable member. Non-rotatable face surface is mounted on an annular slider on the non-rotatable member. A pull-off biasing means urges the annular slider away from the rotatable member and the non-rotatable face surface away from the rotatable surface. A secondary seal is in sealing engagement with the annular slider in the low pressure region and the pull-off biasing means is located radially outwardly of the annular slider in the high pressure region. Biasing means may include coil springs within spring chambers of circumferentially spaced cartridges. Tongues extend inwardly from spring chambers into grooves in slider.
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