公开(公告)号：US20180223732A1

公开(公告)日：2018-08-09

申请号：US15427324

申请日：2017-02-08

Applicant: General Electric Company

Inventor： Jeffrey Donald Clements ,  Darek Tomasz Zatorski ,  Alan Roy Stuart

IPC: F02C3/107 ,  F02C7/36 ,  F02K3/06 ,  F01D5/06 ,  F01D5/22 ,  F01D9/04 ,  F01D25/30 ,  F04D29/32 ,  F04D29/053

CPC classification number: F02C3/107 ,  F02C3/067 ,  F02C7/36 ,  F05D2260/40311 ,  Y02T50/672

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, a gearbox proximate to the turbine section, and a driveshaft. The turbine section includes a first rotating component interdigitated with a second rotating component along the longitudinal direction. The first rotating component includes an outer shroud defining a plurality of outer shroud airfoils extended inward of the outer shroud along the radial direction and one or more connecting airfoils coupling the outer shroud to a radially extended rotor. 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 an input shaft connected to an input gear of the gearbox. The driveshaft is extended in the longitudinal direction and is connected to an output gear of the gearbox. The first rotating component is coupled to the driveshaft.

公开(公告)号：US20170167438A1

公开(公告)日：2017-06-15

申请号：US14966007

申请日：2015-12-11

Applicant: General Electric Company

Inventor： Brandon Wayne Miller ,  Matthew Timothy Franer ,  Alan Roy Stuart

IPC: F02K1/70 ,  F01D15/12 ,  F01D5/12 ,  F02K3/06 ,  F01D25/24 ,  F01D5/02

CPC classification number: F02K1/70 ,  F01D5/02 ,  F01D5/12 ,  F01D15/12 ,  F01D25/16 ,  F01D25/24 ,  F02C7/04 ,  F02K1/06 ,  F02K1/72 ,  F02K3/06 ,  F05D2220/36 ,  F05D2250/10 ,  F05D2250/42

Abstract: A gas turbine engine includes a fan and a core in flow communication with the fan. The core includes an aftmost turbine, and the aftmost turbine includes an aftmost stage of rotor blades. The gas turbine engine also includes a nacelle assembly having a translating and rotating thrust reverser system and enclosing the fan and at least a portion of the core. The nacelle assembly defines a nacelle assembly length between a forward lip and an aft edge. Additionally, the gas turbine engine defines an engine length between the forward lip of the nacelle assembly and the aftmost stage of rotor blades of the aftmost turbine. A ratio of the turbine length to the nacelle assembly length is greater than about 0.5 and less than about 1.

公开(公告)号：US20170159606A1

公开(公告)日：2017-06-08

申请号：US14957908

申请日：2015-12-03

Applicant: General Electric Company

Inventor： Alan Roy Stuart

IPC: F02K1/70 ,  F01D25/24 ,  F02K3/06

CPC classification number: F02K1/70 ,  F01D25/24 ,  F02K1/72 ,  F02K3/06 ,  F05D2220/323 ,  F05D2230/60 ,  Y02T50/672

Abstract: A thrust reverser system for incorporation into a nacelle assembly of a gas turbine engine includes a frame member and a forward ring movable along an axial centerline relative to the frame member. The forward ring is movable between a first position and the second position. The thrust reverser system additionally includes a cascade segment slidably attached to the frame member and rotatably attached to the forward ring. When the forward ring is in the first position the cascade segment is in a radially outer position, and when the forward ring is in the second position, the cascade segment is in a radially inner position for changing a direction of a flow of air to generate reverse thrust.

公开(公告)号：US09016040B2

公开(公告)日：2015-04-28

申请号：US13690065

申请日：2012-11-30

Applicant: General Electric Company

Inventor： Alan Roy Stuart ,  James Michael Cosgrove

IPC: F02K1/72 ,  F02K1/70 ,  F02K1/64

CPC classification number: F02K1/72 ,  F02K1/64 ,  F02K1/70 ,  Y02T50/672

Abstract: A thrust reverser system and operation suitable for high-bypass turbofan engines. The thrust reverser system includes a cascade system adapted to be translated with a translating cowl in an aft direction of an engine to expose a circumferential opening. The cascade system is deployed from a stowed position as the translating cowl and the cascade system are translated in the aft direction. During deployment of the cascade system, a fore end thereof translates in the aft direction and an aft end thereof initially translates in the aft direction and then subsequently rotates about the fore end so that further translation of the cascade segment in the aft direction causes the cascade segment to move to a deployed position and divert bypass air within a bypass duct of the engine through the circumferential opening.

Abstract translation: 推力反向器系统和适用于高旁通涡扇发动机的操作。 推力反向器系统包括级联系统，其适于在发动机的后部方向上与平移的整流罩平移以暴露周向开口。 级联系统从收起位置部署，平移整流罩和级联系统在后方向上平移。 在级联系统的布置期间，其前端在后部方向上平移，并且其后端首先在后方向上平移，然后围绕前端旋转，使得级联段在后方向上的进一步平移导致级联 分段移动到展开位置，并通过周向开口将旁路空气转移到发动机的旁路管道内。

公开(公告)号：US20140150403A1

公开(公告)日：2014-06-05

申请号：US13690065

申请日：2012-11-30

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Alan Roy Stuart ,  James Michael Cosgrove

IPC: F02K1/70

CPC classification number: F02K1/72 ,  F02K1/64 ,  F02K1/70 ,  Y02T50/672

Abstract: A thrust reverser system and operation suitable for high-bypass turbofan engines. The thrust reverser system includes a cascade system adapted to be translated with a translating cowl in an aft direction of an engine to expose a circumferential opening. The cascade system is deployed from a stowed position as the translating cowl and the cascade system are translated in the aft direction. During deployment of the cascade system, a fore end thereof translates in the aft direction and an aft end thereof initially translates in the aft direction and then subsequently rotates about the fore end so that further translation of the cascade segment in the aft direction causes the cascade segment to move to a deployed position and divert bypass air within a bypass duct of the engine through the circumferential opening.

Abstract translation: 推力反向器系统和适用于高旁通涡扇发动机的操作。 推力反向器系统包括级联系统，其适于在发动机的后部方向上与平移的整流罩平移以暴露周向开口。 级联系统从收起位置部署，平移整流罩和级联系统在后方向上平移。 在级联系统的布置期间，其前端在后部方向上平移，并且其后端首先在后方向上平移，然后围绕前端旋转，使得级联段在后方向上的进一步平移导致级联 分段移动到展开位置，并通过周向开口将旁路空气转移到发动机的旁路管道内。