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公开(公告)号：US11802525B2
公开(公告)日：2023-10-31
申请号：US17647425
申请日：2022-01-07
Applicant: General Electric Company
Inventor： Vinod Chaudhari , Bhaskar Nanda Mondal , Kishanjit Pal , Sushilkumar Shevakari , Ian F. Prentice , Thomas Moniz , Trevor H. Wood , Kishore Ramakrishnan
CPC classification number: F02K5/00 , F04D19/002 , F04D29/36
Abstract: An unducted single fan engine includes a housing having one or more fan blades coupled to the housing and configured to rotate circumferentially. The engine has one or more outlet guide vanes coupled to the housing. Each of the one or more guide vanes has a leading edge portion having a variable leading edge. The engine has one or more actuation devices coupled to each of the one or more outlet guide vanes. The one or more actuation devices are configured to control the variable leading edge of the respective outlet guide vane. The variable leading edge is controllable to vary the pitch, camber, lean angle, or sweep of the respective outlet guide vane.
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公开(公告)号：US20230220816A1
公开(公告)日：2023-07-13
申请号：US17647425
申请日：2022-01-07
Applicant: General Electric Company
Inventor： Vinod Chaudhari , Bhaskar Nanda Mondal , Kishanjit Pal , Sushilkumar Shevakari , Ian F. Prentice , Thomas Moniz , Trevor H. Wood , Kishore Ramakrishnan
CPC classification number: F02K5/00 , F04D19/002 , F04D29/36
Abstract: An unducted single fan engine includes a housing having one or more fan blades coupled to the housing and configured to rotate circumferentially. The engine has one or more outlet guide vanes coupled to the housing. Each of the one or more guide vanes has a leading edge portion having a variable leading edge. The engine has one or more actuation devices coupled to each of the one or more outlet guide vanes. The one or more actuation devices are configured to control the variable leading edge of the respective outlet guide vane. The variable leading edge is controllable to vary the pitch, camber, lean angle, or sweep of the respective outlet guide vane.
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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：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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Patent Agency Ranking
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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公开(公告)号：US20210262416A1
公开(公告)日：2021-08-26
申请号：US16796256
申请日：2020-02-20
Applicant: General Electric Company
Inventor： Kishanjit Pal , Bhaskar Nanda Mondal , Lajith Vijayan
Abstract: A gas turbine engine, the engine including a core turbine engine forming a core flowpath, a rotatable first stage blade assembly in which a bypass airflow passage is formed downstream of the first stage blade assembly, and a shroud positioned at the bypass airflow passage radially outward of the core turbine engine, wherein a first flowpath is formed outward of the shroud at which a first portion of air is flowed, and wherein the shroud and the core turbine engine form a second flowpath therebetween, the core flowpath in fluid communication with the second flowpath to flow a mixture of a second portion of air and combustion gases in the second flowpath.
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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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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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