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公开(公告)号：US20210246849A1
公开(公告)日：2021-08-12
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：US20210148243A1
公开(公告)日：2021-05-20
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：US20220010727A1
公开(公告)日：2022-01-13
申请号：US16923198
申请日：2020-07-08
Applicant: General Electric Company
Inventor： Arvind Namadevan , Jeffrey Douglas Rambo , Arnab Sen
IPC: F02C7/18
Abstract: An aspect of the present disclosure is directed to a system for reducing thermal gradient at a heat engine. The heat engine includes a rotor assembly with a rotor disk and a seal assembly is provided. An interfacing structure at least partially surrounds the rotor assembly at the seal assembly. The seal assembly and the interfacing structure together form a first cavity defining a first environmental condition and a second cavity defining a second environmental condition. A fluid supply manifold is connected to the rotor assembly and is extended at least partially along a radial direction from the first cavity to an outlet opening in thermal communication with the rotor disk of the rotor assembly.
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公开(公告)号：US20210388739A1
公开(公告)日：2021-12-16
申请号：US16902480
申请日：2020-06-16
Applicant: General Electric Company
Inventor： Arvind Namadevan , Arnab Sen , Wendy Wenling Lin , Shivam Mittal , Peeyush Pankaj , Shashank Suresh Puranik , Narayanan Payyoor , Praveen Sharma
IPC: F01D25/24
Abstract: A composite fan casing for a gas turbine engine defining a central axis is generally provided. The composite fan casing includes a core having a plurality of core layers of reinforcing fibers bonded together with a thermosetting polymeric resin, wherein one or more of the plurality of core layers of reinforcing fibers comprises a shear thickening fluid. The core layer may include at least one fabric sheet comprising the reinforcing fibers.
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公开(公告)号：US10941706B2
公开(公告)日：2021-03-09
申请号：US15895336
申请日：2018-02-13
Applicant: General Electric Company
Inventor： Arnab Sen , Brandon Wayne Miller , Bhaskar Nanda Mondal , Kishanjit Pal , Daniel Alan Niergarth
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.
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Patent Agency Ranking
公开(公告)号：US20200088037A1
公开(公告)日：2020-03-19
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
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：US20190257247A1
公开(公告)日：2019-08-22
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：US20190249599A1
公开(公告)日：2019-08-15
申请号：US15895336
申请日：2018-02-13
Applicant: General Electric Company
Inventor： Arnab Sen , Brandon Wayne Miller , Bhaskar Nanda Mondal , Kishanjit Pal , Daniel Alan Niergarth
CPC classification number: F02C6/18 , F02C3/04 , F02C7/18 , F02K3/02 , F05D2210/20 , F05D2220/323 , F05D2220/62 , F05D2220/76 , F05D2260/213
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.
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公开(公告)号：US11525400B2
公开(公告)日：2022-12-13
申请号：US16923198
申请日：2020-07-08
Applicant: General Electric Company
Inventor： Arvind Namadevan , Jeffrey Douglas Rambo , Arnab Sen
Abstract: An aspect of the present disclosure is directed to a system for reducing thermal gradient at a heat engine. The heat engine includes a rotor assembly with a rotor disk and a seal assembly is provided. An interfacing structure at least partially surrounds the rotor assembly at the seal assembly. The seal assembly and the interfacing structure together form a first cavity defining a first environmental condition and a second cavity defining a second environmental condition. A fluid supply manifold is connected to the rotor assembly and is extended at least partially along a radial direction from the first cavity to an outlet opening in thermal communication with the rotor disk of the rotor assembly.
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公开(公告)号：US10823184B2
公开(公告)日：2020-11-03
申请号：US15221962
申请日：2016-07-28
Applicant: General Electric Company
Inventor： Arnab Sen , Mohamed Musthafa Thoppil , Nathan Evan McCurdy Gibson
IPC: F01D11/02 , F04D27/00 , F01D11/04 , F16J15/34 , F01D5/02 , F01D9/02 , F01D11/00 , F01D25/10 , F04D29/056 , F04D29/32 , F04D29/54
Abstract: A turbine engine with a stator having axially spaced first and second structural elements along with a rotor and a face seal between the rotor and the stator including a non-rotating gas bearing face coupled to the first and second structural elements, and a rotating gas bearing face coupled to the rotor and confronting the non-rotating gas bearing surface. Introducing airflow to one or multiple parts of the seal.
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