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公开(公告)号：US10814955B2
公开(公告)日：2020-10-27
申请号：US15890785
申请日：2018-02-07
Applicant: General Electric Company
Inventor： Jixian Yao , Nikolai N. Pastouchenko , Patrick John Lonneman , Patrick Michael Marrinan , Richard David Cedar
Abstract: An aircraft includes a boundary layer ingestion fan defining a centerline and including a plurality of fan blades rotatable about the centerline. The aircraft also includes a fuselage extending between a forward end and an aft end along a longitudinal direction, the boundary layer ingestion fan positioned within the fuselage at the aft end of the fuselage, the fuselage defining an inlet upstream of the boundary layer ingestion fan extending at least about 180 degrees around the centerline of the boundary layer ingestion fan, the fuselage further defining an exhaust downstream of the boundary layer ingestion fan.
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公开(公告)号：US10808572B2
公开(公告)日：2020-10-20
申请号：US15943177
申请日：2018-04-02
Applicant: General Electric Company
Inventor： James Michael Hoffman , Jeffrey Ryan Trimmer , Dennis Robert Jonassen , Mark Stephen Zlatic , Patrick John Lonneman
Abstract: A gas turbine engine that includes a turbomachinery core operable to produce a core gas flow and that includes a combustor. A first duct is positioned downstream of and in flow communication with the combustor. A component is positioned within the first duct and extends between radially outward and radially inward walls of the first duct. The component that includes a first cooling passageway formed therein. The first cooling passageway extends between an inlet communicating with the first duct and positioned facing towards the turbomachinery core, and an outlet communicating with a pressure sink.
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公开(公告)号：US20190301301A1
公开(公告)日：2019-10-03
申请号：US15943177
申请日：2018-04-02
Applicant: General Electric Company
Inventor： James Michael Hoffman , Jeffrey Ryan Trimmer , Dennis Robert Jonassen , Mark Stephen Zlatic , Patrick John Lonneman
Abstract: A gas turbine engine that includes a turbomachinery core operable to produce a core gas flow and that includes a combustor. A first duct is positioned downstream of and in flow communication with the combustor. A component is positioned within the first duct and extends between radially outward and radially inward walls of the first duct. The component that includes a first cooling passageway formed therein. The first cooling passageway extends between an inlet communicating with the first duct and positioned facing towards the turbomachinery core, and an outlet communicating with a pressure sink.
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公开(公告)号：US10113508B2
公开(公告)日：2018-10-30
申请号：US14940543
申请日：2015-11-13
Applicant: General Electric Company
Inventor： Alan Roy Stuart , Patrick John Lonneman
Abstract: A gas turbine engine having a centerline axis is provided. The gas turbine engine includes a fan and a fan cowl assembly surrounding the fan to define a bypass duct configured to channel airflow for the fan. The fan cowl assembly includes a stationary cowl and a transcowl. The gas turbine engine further includes a plurality of actuators configured for displacing the transcowl relative to the stationary cowl. Each of the actuators is skewed relative to the centerline axis of the engine.
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Patent Agency Ranking
公开(公告)号：US20160369639A1
公开(公告)日：2016-12-22
申请号：US14746426
申请日：2015-06-22
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Trevor Goerig , Darek Tomasz Zatorski , Tsuguji Nakano , Patrick John Lonneman
CPC classification number: F01D7/00 , F01D5/02 , F01D5/3007 , F01D7/02 , F01D15/00 , F01D25/24 , F02C3/04 , F02K1/66 , F04D27/0246 , F04D29/323 , F05D2220/32 , F05D2220/36 , F05D2240/20 , F05D2240/35 , Y02T50/671 , Y02T50/673
Abstract: An actuation assembly for a variable pitch fan for a gas turbine engine is provided. The actuation assembly generally includes a plurality of fan blades, a scheduling ring, and a plurality of linkage arms. The plurality of fan blades are rotatably coupled to a disk and extend radially therefrom. The scheduling ring is rotatable relative to the disk and has a plurality of slots. Each of the plurality of linkage arms are operatively coupled to one of the plurality of fan blades and to one of the plurality of slots. Each of the plurality of fan blades rotate according to a blade pitch schedule defined by the slot to which it is operatively coupled, and at least two of the plurality of slots define different blade pitch schedules.
Abstract translation: 提供了一种用于燃气涡轮发动机的变桨距风扇的致动组件。 致动组件通常包括多个风扇叶片，调度环和多个连杆臂。 多个风扇叶片可旋转地联接到盘并从其径向延伸。 调度环可相对于盘旋转并具有多个槽。 多个联动臂中的每一个可操作地联接到多个风扇叶片中的一个和多个狭槽中的一个。 多个风扇叶片中的每一个根据由其可操作地联接的狭槽限定的叶片间距调度旋转，并且多个狭槽中的至少两个限定不同的叶片间距调度。
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公开(公告)号：US10465538B2
公开(公告)日：2019-11-05
申请号：US14873324
申请日：2015-10-02
Applicant: General Electric Company
Inventor： Darek Tomasz Zatorski , Patrick John Lonneman , Alan Roy Stuart
Abstract: A gas turbine engine having a forward thrust mode and a reverse thrust mode is provided. The gas turbine engine includes a variable pitch fan configured for generating forward thrust in the forward thrust mode of the engine and reverse thrust in the reverse thrust mode of the engine. The engine also includes a fan cowl surrounding the variable pitch fan, wherein the fan cowl forms a bypass duct for airflow generated by the fan. The fan cowl includes an aft edge that defines a physical flow area of the bypass duct, and a deflection device configured for deflecting airflow near the aft edge, wherein the deflection device is configured for operation in the reverse thrust mode of the engine. The physical flow area of the bypass duct at the aft edge remains the same in the forward thrust mode of the engine and in the reverse thrust mode of the engine.
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7.发明授权公开(公告)号：US10399664B2
公开(公告)日：2019-09-03
申请号：US15145894
申请日：2016-05-04
Applicant: GENERAL ELECTRIC COMPANY
Inventor： William Joseph Bowden , Andrew Breeze-Stringfellow , Richard David Cedar , Syed Arif Khalid , Patrick John Lonneman , Aleksander Piotr Pasieczny , Daniel Lawrence Tweedt
IPC: B64C11/14 , B64D33/02 , F02C6/20 , F02C7/05 , F01D5/02 , F01D9/04 , F01D25/04 , F01D25/24 , F04D29/32 , F04D29/38 , B64D27/00
Abstract: An unducted thrust producing system is provided that can include a rotating element having an axis of rotation about a central longitudinal axis and comprising a plurality of blades attached to a spinner; a stationary element positioned aft of the rotating element; and an inlet positioned between the rotating element and the stationary element such that the inlet passes radially inward of the stationary element. The rotating element defines an annular valley positioned between a first annular crown and a second annular crown, and the inlet defines an open area positioned aft of the second annular crown.
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公开(公告)号：US20190241248A1
公开(公告)日：2019-08-08
申请号：US15890785
申请日：2018-02-07
Applicant: General Electric Company
Inventor： Jixian Yao , Nikolai N. Pastouchenko , Patrick John Lonneman , Patrick Michael Marrinan , Richard David Cedar
Abstract: An aircraft includes a boundary layer ingestion fan defining a centerline and including a plurality of fan blades rotatable about the centerline. The aircraft also includes a fuselage extending between a forward end and an aft end along a longitudinal direction, the boundary layer ingestion fan positioned within the fuselage at the aft end of the fuselage, the fuselage defining an inlet upstream of the boundary layer ingestion fan extending at least about 180 degrees around the centerline of the boundary layer ingestion fan, the fuselage further defining an exhaust downstream of the boundary layer ingestion fan.
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公开(公告)号：US09835037B2
公开(公告)日：2017-12-05
申请号：US14746426
申请日：2015-06-22
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Trevor Goerig , Darek Tomasz Zatorski , Tsuguji Nakano , Patrick John Lonneman
IPC: F02C3/04 , F01D7/00 , F04D27/02 , F04D29/32 , F01D5/02 , F01D5/30 , F01D15/00 , F01D25/24 , F02K1/66 , F01D7/02
CPC classification number: F01D7/00 , F01D5/02 , F01D5/3007 , F01D7/02 , F01D15/00 , F01D25/24 , F02C3/04 , F02K1/66 , F04D27/0246 , F04D29/323 , F05D2220/32 , F05D2220/36 , F05D2240/20 , F05D2240/35 , Y02T50/671 , Y02T50/673
Abstract: An actuation assembly for a variable pitch fan for a gas turbine engine is provided. The actuation assembly generally includes a plurality of fan blades, a scheduling ring, and a plurality of linkage arms. The plurality of fan blades are rotatably coupled to a disk and extend radially therefrom. The scheduling ring is rotatable relative to the disk and has a plurality of slots. Each of the plurality of linkage arms are operatively coupled to one of the plurality of fan blades and to one of the plurality of slots. Each of the plurality of fan blades rotate according to a blade pitch schedule defined by the slot to which it is operatively coupled, and at least two of the plurality of slots define different blade pitch schedules.
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