General Electric Company

Guohua Zhong

Yao Li

Ning Fang

William Joseph Bowden

Liangjun Qiu

Li Yao

Bartosz Karbowski

Qiang Pang

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.

Scoop inlet

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.

Method and system for mitigation of cavity resonance

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.

Aircraft with injection cooling system and injection cooling system

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Shanghai, China

Guohua Zhong