公开(公告)号：US10161311B2

公开(公告)日：2018-12-25

申请号：US15104479

申请日：2013-12-23

Applicant: General Electric Company

Inventor： Qiang Pang ,  Guohua Zhong ,  Yao Li

IPC: F02C7/18 ,  F02K1/70 ,  F02K1/72 ,  F02K1/76 ,  F02C6/08 ,  B64D27/16 ,  B64D29/00 ,  F02K3/06

Abstract: An aircraft with aturbofan engine assembly having at least one compressor, a nacelle surrounding the turbine engine and defimng an annular bypass duct between the nacelle and the turbine engine, a thrust reverser having at least one moveable control surface, a thrust reverser locking system configured to selectively lock the thrust reverserand an injection cooling system.

公开(公告)号：US10544737B2

公开(公告)日：2020-01-28

申请号：US15335795

申请日：2016-10-27

Applicant: GENERAL ELECTRIC COMPANY

Inventor： William Joseph Bowden ,  Ning Fang ,  Guohua Zhong ,  Bartosz Karbowski

IPC: F02C7/24 ,  F02C6/08 ,  F02C9/18 ,  F02K3/06

Abstract: A turbofan engine includes a core engine, a fan, a fan bypass duct partially surrounding the core engine and the fan, and a bleed system. The bleed system includes a first bleed circuit configured to bleed pressurized air from the core engine and channel the flow to a first circuit of a heat exchanger, and a second bleed circuit configured to bleed fan air from the fan bypass duct and channel the flow to a second circuit of the heat exchanger. The second bleed circuit includes a bleed duct including a duct inlet and a duct outlet coupled in flow communication with the heat exchanger through a valve. The bleed duct also includes an acoustic suppression conduit extending from the bleed duct upstream of the valve to the fan bypass duct and sized to suppress pressure oscillations inside the second bleed circuit when the valve is at least partially closed.

公开(公告)号：US20240328324A1

公开(公告)日：2024-10-03

申请号：US18621779

申请日：2024-03-29

Applicant: General Electric Company

Inventor： Ning Fang ,  William Bowden ,  Weili Yang ,  Keith E. Blodgett ,  Guohua Zhong ,  Niloufar Hosseiny

IPC: F01D11/00 ,  F01D25/24

CPC classification number: F01D11/005 ,  F01D25/24 ,  F05D2220/323 ,  F05D2240/56

Abstract: Apparatus are disclosed for a turbofan comprising: a bifurcation including a first track; and an outer casing including an airflow inlet and an airflow outlet, the outer casing adjustable into a closed position and an open position, the outer casing positioned around the bifurcation, the outer casing including a first slider for movement between the closed position and the open position that mates with the first track, the first track including a brush seal holder and a brush seal including a plurality of bristles having a compressed state in the closed position and a decompressed state in the open position.

公开(公告)号：US11162417B2

公开(公告)日：2021-11-02

申请号：US16419499

申请日：2019-05-22

Applicant: General Electric Company

Inventor： Liangjun Qiu ,  Guohua Zhong

IPC: F02C6/08 ,  F02C7/04 ,  F02C7/18 ,  F02C3/06

Abstract: A scoop inlet for a turbomachine. The turbomachine includes a core engine casing relative to a centerline extending the length of the turbomachine. Further, the core engine casing at least partially defines a bypass flow passage. The scoop inlet includes an inlet at the core engine casing in fluid communication with the bypass flow passage. The inlet includes a mouth fluidly coupling the bypass flow passage to a cooling system. The mouth receives bypass bleed air from the bypass flow passage and defines a width in a circumferential direction relative to the centerline. The scoop inlet also includes a bypass bleed duct defined through the core engine casing. The bypass bleed duct fluidly couples the mouth to the cooling system. In addition, the scoop inlet includes a plurality of droplets at the mouth of the inlet partially extending from the mouth into the bypass flow passage.