Fan nacelle trailing edge

A fan nacelle, a gas turbine engine cell assembly, and an aircraft are provided. The fan nacelle includes a fan duct skin arranged in a fan duct to direct airflow from the fan of a turbofan engine toward a fan nozzle. An exterior skin of the fan nacelle directs air flow around an exterior of the engine. The fan duct skin and the exterior skin terminate at a trailing edge, and a trailing edge portion of the exterior skin is one of parallel to and diverging from a trailing edge portion of the fan duct skin in an aft direction. In certain aspects, the trailing edge portion of the exterior skin isactuatable or inflatable to selectively divert from the trailing edge portion of the fan duct skin. 本申请提供风机短舱、燃气涡轮发动机单元总成和飞行器。该风机短舱包括布置在风机气道中的风机气道蒙皮，以将气流从涡轮风机发动机的风机朝向风机喷嘴引导。该风机短舱的外蒙皮引导空气围绕发动机的外部流动。该风机气道蒙皮和该外蒙皮在后缘处终止，并且该外蒙皮的后缘部分是在向后方向上与该风机气道蒙皮的后缘部分平行和在向后方向上从风机气道蒙皮的后缘部分偏离中的种。在某些方面，该外蒙皮的后缘部分是可致动的或可充气的，以从该风机气道蒙皮的后缘部分选择性转向。