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公开(公告)号：US20240093642A1
公开(公告)日：2024-03-21
申请号：US18524874
申请日：2023-11-30
Inventor： Paul Hadley Vitt , Michael Simonetti , Ashish Sharma
CPC classification number: F02C7/141 , F01D25/12 , F02C7/16 , F05D2220/32 , F05D2230/60 , F05D2260/205 , F05D2260/232
Abstract: A gas turbine engine includes a fan located at a forward portion of the gas turbine engine, 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 at least a portion of the compressor section and with at least a portion of the turbine section. An outlet guide vane assembly includes multiple outlet guide vanes located in an exhaust airflow path downstream of the turbine section. The multiple outlet guide vanes being spaced-apart circumferentially from each other over an angular range of about 360 degrees, and each multiple outlet guide vane defining a radial extent. At least one of the multiple outlet guide vanes includes a cold fluid passageway and another of the multiple guide vanes includes a heated fluid passageway.
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公开(公告)号：US20250027721A1
公开(公告)日：2025-01-23
申请号：US18349415
申请日：2023-07-10
Applicant: General Electric Company
Inventor： Michael Simonetti , Michael Vadnais , Nishita Deshmukh , Ramana Reddy Kollam , James Fitzgerald Bonar , Mehmet Kilic , Prerna Mandal
IPC: F28D7/16
Abstract: A gas turbine engine is provided. The gas turbine engine includes: a thermal management system having a thermal fluid member having a flow of thermal fluid therethrough during operation of the gas turbine engine and a heat exchanger assembly, the heat exchanger assembly including: a core section comprising a plurality of heat exchange members; and a heat exchange manifold including a first direction pressure vessel in fluid communication with the thermal fluid member and a second direction pressure vessel extending from the first direction pressure vessel, the first and second direction pressure vessels each extending in a reference plane, the second direction pressure vessel in fluid communication with the first direction pressure vessel and with at least one of the plurality of heat exchange members.
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Patent Agency Ranking
公开(公告)号：US12259194B2
公开(公告)日：2025-03-25
申请号：US18349415
申请日：2023-07-10
Applicant: General Electric Company
Inventor： Michael Simonetti , Michael Vadnais , Nishita Deshmukh , Ramana Reddy Kollam , James Fitzgerald Bonar , Mehmet Kilic , Prerna Mandal
Abstract: A gas turbine engine is provided. The gas turbine engine includes: a thermal management system having a thermal fluid member having a flow of thermal fluid therethrough during operation of the gas turbine engine and a heat exchanger assembly, the heat exchanger assembly including: a core section comprising a plurality of heat exchange members; and a heat exchange manifold including a first direction pressure vessel in fluid communication with the thermal fluid member and a second direction pressure vessel extending from the first direction pressure vessel, the first and second direction pressure vessels each extending in a reference plane, the second direction pressure vessel in fluid communication with the first direction pressure vessel and with at least one of the plurality of heat exchange members.
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公开(公告)号：US20230043809A1
公开(公告)日：2023-02-09
申请号：US17388618
申请日：2021-07-29
Applicant: General Electric Company
Inventor： Scott Alan Schimmels , Jeffrey Douglas Rambo , Daniel Alan Niergarth , Daniel Lawrence Tweedt , Michael Simonetti , Michael Julian Castillo , Timothy Richard DePuy , Steven Benjamin Morris
Abstract: A gas turbine engine is provided including a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order; a rotor assembly driven by the turbomachine, the rotor assembly, the turbomachine, or both comprising a substantially annular duct relative to the centerline of the gas turbine engine, the annular duct defining a flowpath; a heat exchanger positioned within the annular duct and extending substantially continuously along the circumferential direction, the heat exchanger comprising a first material defining a heat exchange surface exposed to the flowpath, wherein the first material defines a heat exchange coefficient and wherein the heat exchange surface defines a surface area (A), and wherein the heat exchanger has an effective transmission loss (ETL) of between 5 decibels and 1 decibel for an operating condition.
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公开(公告)号：US11867121B2
公开(公告)日：2024-01-09
申请号：US17211345
申请日：2021-03-24
Inventor： Paul Hadley Vitt , Michael Simonetti , Ashish Sharma
CPC classification number: F02C7/141 , F01D25/12 , F02C7/16 , F05D2220/32 , F05D2230/60 , F05D2260/205 , F05D2260/232
Abstract: A gas turbine engine includes a fan located at a forward portion of the gas turbine engine, 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 at least a portion of the compressor section and with at least a portion of the turbine section. An outlet guide vane assembly includes multiple outlet guide vanes located in an exhaust airflow path downstream of the turbine section. The multiple outlet guide vanes being spaced-apart circumferentially from each other over an angular range of about 360 degrees, and each multiple outlet guide vane defining a radial extent. At least one of the multiple outlet guide vanes includes a cold fluid passageway extending at least partially radially therethrough through which a fluid coolant flows and another of the multiple guide vanes includes a heated fluid passageway extending at least partially radially therethrough through which the fluid coolant flows and receives heat from exhaust airflow from the core airflow path.
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公开(公告)号：US20250035382A1
公开(公告)日：2025-01-30
申请号：US18349395
申请日：2023-07-10
Applicant: General Electric Company
Inventor： Michael Simonetti , Michael Vadnais , Nishita Deshmukh , Ramana Reddy Kollam , James Fitzgerald Bonar , Mehmet Kilic , Prerna Mandal
Abstract: A gas turbine engine is provided. The gas turbine engine includes: a thermal management system having a thermal fluid member having a flow of thermal fluid therethrough during operation of the gas turbine engine and a heat exchanger assembly, the heat exchanger assembly including: a core section comprising a plurality of heat exchange members; and a heat exchange manifold including a first direction pressure vessel in fluid communication with the thermal fluid member and a second direction pressure vessel extending from the first direction pressure vessel, the first and second direction pressure vessels each extending in a reference plane, the second direction pressure vessel in fluid communication with the first direction pressure vessel and with at least one of the plurality of heat exchange members.
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公开(公告)号：US20220307418A1
公开(公告)日：2022-09-29
申请号：US17211345
申请日：2021-03-24
Inventor： Paul Hadley Vitt , Michael Simonetti , Ashish Sharma
Abstract: A gas turbine engine includes a fan located at a forward portion of the gas turbine engine, 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 at least a portion of the compressor section and with at least a portion of the turbine section. An outlet guide vane assembly includes multiple outlet guide vanes located in an exhaust airflow path downstream of the turbine section. The multiple outlet guide vanes being spaced-apart circumferentially from each other over an angular range of about 360 degrees, and each multiple outlet guide vane defining a radial extent. At least one of the multiple outlet guide vanes includes a cold fluid passageway extending at least partially radially therethrough through which a fluid coolant flows and another of the multiple guide vanes includes a heated fluid passageway extending at least partially radially therethrough through which the fluid coolant flows and receives heat from exhaust airflow from the core airflow path.
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