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公开(公告)号：US20230073647A1
公开(公告)日：2023-03-09
申请号：US17470261
申请日：2021-09-09
Applicant: General Electric Company
Inventor： John Carl Glessner , Daniel John Oehrle , Mark Edward Linz
IPC: F02C9/18
Abstract: A gas turbine engine includes a turbomachine defining a core flowpath extending through a first compressor and a second compressor, wherein a first compressor frame defines a compressor bypass passage extending from the core flowpath at the first compressor frame; and a forward compressor frame positioned between the first compressor and the second compressor, wherein the forward compressor frame defines at least in part a second portion of the core flowpath at a location downstream of the first portion of the core flowpath, wherein the forward compressor frame defines a compressor bleed passage extending from the core flowpath at a location downstream of the first compressor and upstream of the second compressor to egress a flow of air away from the core flowpath.
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公开(公告)号：US20230250733A1
公开(公告)日：2023-08-10
申请号：US18295897
申请日：2023-04-05
Applicant: GENERAL ELECTRIC COMPANY
Inventor： John Carl Glessner , Mark Edward Linz
IPC: F01D25/24
CPC classification number: F01D25/24 , F05D2220/323 , F05D2240/14
Abstract: A turbine engine including an engine core, a nacelle, and a cowl door. The engine core including in serial, axial flow arrangement a compressor section, a combustor section, and a turbine section and defining a first airflow axially through the engine core. The nacelle circumscribing at least a portion of the engine core and having an exterior surface defining a second airflow along the exterior surface and an internal passage located between the exterior surface and the engine core and defining a third airflow. The cowl door located along the nacelle.
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公开(公告)号：US12018575B2
公开(公告)日：2024-06-25
申请号：US18295897
申请日：2023-04-05
Applicant: GENERAL ELECTRIC COMPANY
Inventor： John Carl Glessner , Mark Edward Linz
IPC: F01D25/24
CPC classification number: F01D25/24 , F05D2220/323 , F05D2240/14
Abstract: A turbine engine including an engine core, a nacelle, and a cowl door. The engine core including in serial, axial flow arrangement a compressor section, a combustor section, and a turbine section and defining a first airflow axially through the engine core. The nacelle circumscribing at least a portion of the engine core and having an exterior surface defining a second airflow along the exterior surface and an internal passage located between the exterior surface and the engine core and defining a third airflow. The cowl door located along the nacelle.
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Patent Agency Ranking
公开(公告)号：US20230010841A1
公开(公告)日：2023-01-12
申请号：US17368214
申请日：2021-07-06
Applicant: GENERAL ELECTRIC COMPANY
Inventor： John Carl Glessner , Mark Edward Linz
IPC: F01D25/24
Abstract: An unducted fan turbine engine comprising an engine core including a first airflow, and a nacelle circumscribing at least a portion of the engine core and having an exterior surface defining a second airflow. The nacelle further comprising an internal passage between the exterior surface and the engine core, the internal passage defining a third airflow. The unducted fan turbine engine further comprising a plurality of rotatable fan blades extending radially beyond the exterior surface of the nacelle, and a cowl door located in the nacelle.
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公开(公告)号：US20160348588A1
公开(公告)日：2016-12-01
申请号：US14607401
申请日：2015-01-28
Applicant: General Electric Company
Inventor： Steven Alan Ross , Mark Edward Linz , Joseph Daniel Garrett, III , Amid Ansari , Joseph Roger Broda , Thomas Earl Gillingham , Kevin Richard Graziano , Robert Charles Hon , Kenneth Kirchmayer , Daniel Roy Kiracofe , Andrew Todd Lehmann , Michael Scott McCambrige , Tod Robert Steen , Thomas Charles Swager
Abstract: A method of starting a gas turbine engine having a rotor comprising at least a shaft mounted compressor and turbine, with a casing surrounding the rotor.
Abstract translation: 一种起动具有转子的燃气涡轮发动机的方法，所述转子至少包括轴安装的压缩机和涡轮机，其中壳体围绕转子。
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公开(公告)号：US12085027B2
公开(公告)日：2024-09-10
申请号：US17470261
申请日：2021-09-09
Applicant: General Electric Company
Inventor： John Carl Glessner , Daniel John Oehrle , Mark Edward Linz
IPC: F02C9/18
CPC classification number: F02C9/18 , F05D2220/32
Abstract: A gas turbine engine includes a turbomachine defining a core flowpath extending through a first compressor and a second compressor, wherein a first compressor frame defines a compressor bypass passage extending from the core flowpath at the first compressor frame; and a forward compressor frame positioned between the first compressor and the second compressor, wherein the forward compressor frame defines at least in part a second portion of the core flowpath at a location downstream of the first portion of the core flowpath, wherein the forward compressor frame defines a compressor bleed passage extending from the core flowpath at a location downstream of the first compressor and upstream of the second compressor to egress a flow of air away from the core flowpath.
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公开(公告)号：US11639671B2
公开(公告)日：2023-05-02
申请号：US17368214
申请日：2021-07-06
Applicant: GENERAL ELECTRIC COMPANY
Inventor： John Carl Glessner , Mark Edward Linz
IPC: F01D25/24
Abstract: An unducted fan turbine engine comprising an engine core including a first airflow, and a nacelle circumscribing at least a portion of the engine core and having an exterior surface defining a second airflow. The nacelle further comprising an internal passage between the exterior surface and the engine core, the internal passage defining a third airflow. The unducted fan turbine engine further comprising a plurality of rotatable fan blades extending radially beyond the exterior surface of the nacelle, and a cowl door located in the nacelle.
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公开(公告)号：US11268446B2
公开(公告)日：2022-03-08
申请号：US16683704
申请日：2019-11-14
Applicant: General Electric Company
Inventor： Joseph Daniel Garrett, III , Mark Edward Linz , Tod Robert Steen , Thomas Charles Swager , Andrew Todd Lehmann , Michael Scott McCambridge , Robert Charles Hon , Thomas Earl Gillingham , Daniel Roy Kiracofe , Kenneth Kirchmayer , Joseph Roger Broda , Kevin Richard Graziano , Steven Alan Ross , Amid Ansari
Abstract: A gas turbine engine and method of starting, the gas turbine engine having a rotor comprising at least a shaft mounted compressor and turbine, with a casing surrounding the rotor. The method comprises an acceleration phase, a bowed-rotor cooling phase, during the acceleration, and a combustion phase. The bowed-rotor cooling phase comprises a time where the rotational speed of the rotor is maintained below a bowed-rotor threshold speed until a non-bowed condition is satisfied, wherein the air forced through the gas turbine engine cools the rotor. The combustion phase occurs after the bowed-rotor cooling phase and upon reaching the combustion speed, wherein fuel is supplied to the gas turbine engine is turned on.
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