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公开(公告)号：US20250075662A1
公开(公告)日：2025-03-06
申请号：US18461078
申请日：2023-09-05
Applicant: GENERAL ELECTRIC COMPANY
Inventor： John Carl Glessner , Stephen G. Matava
Abstract: A turbine engine having an inner cowl that circumscribes at least a portion of an engine core, where the inner cowl is radially spaced from the engine core to define an inner cowl space. An outer cowl circumscribes at least a portion of the inner cowl where the outer cowl includes a radially outer surface spaced from a radially inner surface to define an outer cowl space. A fairing extends radially between the inner cowl and the outer cowl. A first accessory gearbox is located in the inner cowl space and the fairing. A second accessory gearbox is located in the outer cowl space and operably couples to the first accessory gearbox.
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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：US20240110515A1
公开(公告)日：2024-04-04
申请号：US18071722
申请日：2022-11-30
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Andrew Hudecki , Steven Douglas Johnson , Eric Barre , John Carl Glessner , Efren Souza Chavez
CPC classification number: F02C7/18 , F01D25/12 , F05D2220/323 , F05D2260/232
Abstract: A gas turbine engine including: a fan assembly comprising a fan; and a turbomachine drivingly coupled to the fan and including a compressor section, a combustion section, and a turbine section arranged in serial flow order and defining in part a working gas flowpath, the gas turbine engine defining a bypass passage over the turbomachine; the turbomachine further including a heat exchanger and defining an annular cooling passage extending between an inlet and an outlet, the inlet in airflow communication with the working gas flowpath at a location upstream of the compressor section and the outlet in airflow communication with the bypass passage, the heat exchanger in thermal communication with an airflow through the cooling passage.
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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：US20230119477A1
公开(公告)日：2023-04-20
申请号：US18085714
申请日：2022-12-21
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , John Carl Glessner , Lawrence William Nurre , Ian Francis Prentice , Ethan Patrick O'Connor , Arthur William Sibbach
Abstract: A turbine engine that includes an engine core, an inner cowl, an outer cowl and an accessory gearbox. The engine core includes at least a compressor section, a combustion section, and a turbine section in axial flow arrangement. The accessory gearbox is operably coupled to the engine core and includes a first portion and a second portion.
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Patent Agency Ranking
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：US11572838B2
公开(公告)日：2023-02-07
申请号：US17037027
申请日：2020-09-29
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , John Carl Glessner , Lawrence William Nurre , Ian Francis Prentice , Ethan Patrick O'Connor , Arthur William Sibbach
Abstract: A turbine engine that includes an engine core, an inner cowl, an outer cowl and an accessory gearbox. The engine core includes at least a compressor section, a combustion section, and a turbine section in axial flow arrangement. The accessory gearbox is operably coupled to the engine core and includes a first portion and a second portion.
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公开(公告)号：US20220099031A1
公开(公告)日：2022-03-31
申请号：US17037027
申请日：2020-09-29
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , John Carl Glessner , Lawrence William Nurre , Ian Francis Prentice , Ethan Patrick O'Connor , Arthur William Sibbach
Abstract: A turbine engine that includes an engine core, an inner cowl, an outer cowl and an accessory gearbox. The engine core includes at least a compressor section, a combustion section, and a turbine section in axial flow arrangement. The accessory gearbox is operably coupled to the engine core and includes a first portion and a second portion.
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公开(公告)号：US20140077116A1
公开(公告)日：2014-03-20
申请号：US13623705
申请日：2012-09-20
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Gabriel Walker Santiago , Mustapha Ismail , Jeffrey Scott Laubenthal , John Carl Glessner , James Darrell Bradley , David William Morris, II
IPC: F16K1/00
CPC classification number: F01D17/141 , F01D11/24 , F01D17/24 , F01D17/26 , F01D25/12 , F05D2250/41 , F05D2270/112 , F05D2270/44 , F05D2270/58 , F05D2270/64 , Y02T50/675
Abstract: Methods and systems for operating an integrated actuator are provided. The integrated actuator comprises an actuator body, an extension rod coupled to the actuator body. The extension rod includes a piston valve and is configured for selective movement between a first position in a first mode of operation where the piston valve is fully open and a second position in a second mode of operation where the piston valve is less than fully open. The integrated actuator further comprises a flow body coupled to the actuator body such that the flow body houses the piston valve and a modulation device coupled to the extension rod. The modulation device is operable by movement of the extension rod and is configured to be fully open in the first mode of operation and is configured to be less than fully open in the second mode of operation.
Abstract translation: 提供了用于操作集成致动器的方法和系统。 集成致动器包括致动器主体，连接到致动器主体的延伸杆。 延伸杆包括活塞阀，并且构造成用于在活塞阀完全打开的第一操作模式的第一位置和活塞阀小于完全打开的第二操作模式中的第二位置之间进行选择性运动。 集成致动器还包括联接到致动器本体的流动体，使得流体容纳活塞阀和连接到延伸杆的调制装置。 调制装置可通过延伸杆的移动来操作，并且被配置为在第一操作模式下完全打开，并且被配置为在第二操作模式中小于完全打开。
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公开(公告)号：US12173658B2
公开(公告)日：2024-12-24
申请号：US18085714
申请日：2022-12-21
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , John Carl Glessner , Lawrence William Nurre , Ian Francis Prentice , Ethan Patrick O'Connor , Arthur William Sibbach
Abstract: A turbine engine that includes an engine core, an inner cowl, an outer cowl and an accessory gearbox. The engine core includes at least a compressor section, a combustion section, and a turbine section in axial flow arrangement. The accessory gearbox is operably coupled to the engine core and includes a first portion and a second portion.
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