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公开(公告)号：US20170259929A1
公开(公告)日：2017-09-14
申请号：US15066403
申请日：2016-03-10
Applicant: General Electric Company
Inventor： Alan Roy Stuart
CPC classification number: B64D27/26 , B64D27/18 , B64D2027/268 , F02C7/20 , F05D2220/323 , F05D2230/60 , F05D2240/90 , Y02T50/44 , Y02T50/671
Abstract: A system for mounting an engine to an aircraft includes a rigid structure coupled to a wing and including a forward mount interface and an aft mount interface. The system includes a frame including a first support connection and a second support connection spaced apart from the first support connection. A linkage structure couples the frame to the rigid structure and includes a first linkage pair extending between the forward mount interface and the first support connection at a first angle with respect to a rotational axis, and a second linkage pair extending between the aft mount interface and the second support connection at a second angle with respect to the rotational axis.
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公开(公告)号：US09726113B2
公开(公告)日：2017-08-08
申请号：US14149511
申请日：2014-01-07
Applicant: General Electric Company
Inventor： Robert Joseph Orlando , Thomas Ory Moniz , Alan Roy Stuart
CPC classification number: F02K3/072 , F02C7/36 , F05D2220/323 , F05D2220/327 , Y10T29/49229
Abstract: A turbine engine assembly is provided. The turbine engine assembly includes a core gas turbine engine including a first rotatable drive shaft, a first low-pressure turbine section in serial flow communication with the gas turbine engine, a gear assembly coupled to the first low-pressure turbine section through a second rotatable drive shaft, and a second low-pressure turbine section in serial flow communication with the core gas turbine engine. The first low-pressure turbine section is configured to rotate in a first rotational direction, and the second low-pressure turbine section is configured to rotate in a second rotational direction opposite the first rotational direction. The first and second low-pressure turbine sections are spaced axially apart from each other. The turbine engine assembly also includes a fan assembly coupled to the first low-pressure turbine section through the gear assembly, and coupled to the second low-pressure turbine section through a third rotatable drive shaft.
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43.发明申请THRUST REVERSER SYSTEM WITH TRANSLATING-ROTATING BLOCKER DOORS AND METHOD OF OPERATION 有权具有翻转旋转挡板门的翻转系统和操作方法公开(公告)号：US20140353399A1
公开(公告)日：2014-12-04
申请号：US13689981
申请日：2012-11-30
Applicant: General Electric Company
Inventor： Alan Roy Stuart , James Michael Cosgrove
IPC: F02K1/56
CPC classification number: F02K1/72 , F05D2260/50 , Y02T50/672
Abstract: A thrust reverser system and operation suitable for turbofan engines. Blocker doors of the thrust reverser system have stowed positions in which each door is disposed between a fixed structure and a translating cowl of the engine. The translating cowl is translated in an aft direction of the engine to define at least one opening with the fixed structure, after which the translating cowl is further translated aft to deploy linkage mechanisms that are received in slots recessed into the blocker doors and pivotably connect the doors to the fixed structure. Deployment of the linkage mechanisms from the slots causes the blocker doors to rotate to a deployed position in which each door extends across a bypass duct of the engine and diverts bypass air within the duct through the opening.
Abstract translation: 推力反向器系统和适用于涡轮风扇发动机的操作。 推力反向器系统的阻挡门已经收起每个门设置在发动机的固定结构和平移罩之间的位置。 平移整流罩在发动机的后部方向上平移以限定具有固定结构的至少一个开口，之后平移的整流罩进一步向后平移，以展开连接机构，该连接机构被容纳在凹入到阻挡门中的槽中并可枢转地连接 门到固定结构。 连接机构从狭槽的部署导致阻挡门转动到展开位置，在该展开位置，每个门延伸穿过发动机的旁路管道，并通过开口转移管道内的旁路空气。
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公开(公告)号：US11280198B2
公开(公告)日：2022-03-22
申请号：US16675918
申请日：2019-11-06
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Arnab Sen , Jeffrey Douglas Rambo , Rajesh Kumar , Bhaskar Nanda Mondal , Alan Roy Stuart , Robert Proctor , Christopher Charles Glynn
IPC: F01D5/24 , F01D5/08 , F01D1/24 , F02K3/072 , F01D11/00 , F02C7/18 , F01D25/14 , F02C7/12 , F01D1/26
Abstract: An apparatus for a turbine engine comprising an outer casing, an engine core provided within outer casing and having a at least one set of blades, and through which gasses flow in a forward to aft direction, an outer drum located within the outer casing to define an annular cavity. A set of seals extending between the first surface and the second surface to define at least one cooled cavity within the annular cavity.
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公开(公告)号：US11021970B2
公开(公告)日：2021-06-01
申请号：US16280586
申请日：2019-02-20
Applicant: General Electric Company
Inventor： Alan Roy Stuart , Thomas Ory Moniz
Abstract: A method includes installing a first stage assembly including a first ring member and a first stage of rotor blades, the first ring member defining a first end and the first stage of rotor blades defining a second end; installing a second stage assembly including a second ring member and a second stage of rotor blades, the second ring member defining a first end and the second stage of rotor blades defining a second end, wherein installing the second stage assembly includes fitting the first end of the second ring member to the second end of the first stage of rotor blades to form a first attachment interface; and pressing the second stage assembly against the first stage assembly to fix the first attachment interface.
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Patent Agency Ranking
公开(公告)号：US20210108597A1
公开(公告)日：2021-04-15
申请号：US16811368
申请日：2020-03-06
Applicant: General Electric Company
Inventor： David Marion Ostdiek , Alan Roy Stuart , Daniel Alan Niergarth , Gert Johannes van der Merwe , Brandon Wayne Miller , Stephen William Freund
Abstract: A propulsion system, the propulsion system comprising a rotating element, a stationary element, and an inlet between the rotating element and the stationary element, wherein the inlet passes radially inward of the stationary element; wherein the inlet passes radially inward of the stationary element; wherein the inlet leads to an inlet duct containing a ducted fan having an axis of rotation and a plurality of blades; and wherein the inlet duct divides into a first duct and a second duct, separate from the first duct. A method of operating a propulsion system, comprising the steps of: operating a first rotating fan assembly to produce a first stream of air; directing a portion of the first stream of air into a second ducted rotating fan assembly; operating the second ducted rotating fan assembly to produce a second stream of air; dividing the second stream of air into a core stream and a fan stream; and directing the core stream into a gas turbine engine core.
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公开(公告)号：US10801442B2
公开(公告)日：2020-10-13
申请号：US15427340
申请日：2017-02-08
Applicant: General Electric Company
Inventor： Jeffrey Donald Clements , Darek Tomasz Zatorski , Alan Roy Stuart
Abstract: The present disclosure is directed to a gas turbine engine defining a longitudinal direction, a radial direction, and a circumferential direction, and an upstream end and a downstream end along the longitudinal direction. The gas turbine engine includes a turbine section and a gear assembly within or downstream of the turbine section. The turbine section includes a first rotating component and a second rotating component along the longitudinal direction. The first rotating component includes one or more connecting airfoils coupled to a radially extended rotor, and the second rotating component includes an inner shroud defining a plurality of inner shroud airfoils extended outward of the inner shroud along the radial direction. The second rotating component is coupled to a second shaft connected to an input accessory of the gear assembly, and the first rotating component is coupled to an output accessory of the gear assembly. The output accessory rotates the first rotating component about the axial centerline at a first speed and wherein the second rotating component rotates about the axial centerline at a second speed.
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公开(公告)号：US20200263769A1
公开(公告)日：2020-08-20
申请号：US16280568
申请日：2019-02-20
Applicant: General Electric Company
Inventor： Thomas Ory Moniz , Alan Roy Stuart
Abstract: An engine includes a static frame member; a spool configured to rotate relative to the static frame member during operation of the engine; a gearbox coupled to the spool; and a gearbox coupling assembly mounting the gearbox to the static frame member using a plurality of moveable connection members, each moveable connection member including a sliding connection allowing for movement of the gearbox relative to the static frame member in a plane perpendicular to an axial direction of the engine.
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公开(公告)号：US20200263611A1
公开(公告)日：2020-08-20
申请号：US16280548
申请日：2019-02-20
Applicant: General Electric Company
Inventor： Alan Roy Stuart , Thomas Ory Moniz
IPC: F02C7/36
Abstract: A gas turbine engine includes a frame member extending generally along an axial direction and defining a plurality of slots spaced along a circumferential direction; and a gearbox including a ring gear, a plurality of planet gears, and a sun gear, the plurality of planet gears each positioned at least partially in a respective slot of the plurality of slots defined by the frame member such that the frame member extends through the gearbox.
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公开(公告)号：US20200263555A1
公开(公告)日：2020-08-20
申请号：US16280586
申请日：2019-02-20
Applicant: General Electric Company
Inventor： Alan Roy Stuart , Thomas Ory Moniz
Abstract: A method includes installing a first stage assembly including a first ring member and a first stage of rotor blades, the first ring member defining a first end and the first stage of rotor blades defining a second end; installing a second stage assembly including a second ring member and a second stage of rotor blades, the second ring member defining a first end and the second stage of rotor blades defining a second end, wherein installing the second stage assembly includes fitting the first end of the second ring member to the second end of the first stage of rotor blades to form a first attachment interface; and pressing the second stage assembly against the first stage assembly to fix the first attachment interface.
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