MITIGATION OF ADVERSE FLOW CONDITIONS IN A NACELLE INLET

The invention relates to mitigation of adverse flow conditions in a nacelle inlet. An airflow proximate to leading edges of a turbofan nacelle is ejected substantially normal to a fan face of the turbofan, creating suction proximate to the leading edge and mitigating flow separation proximate to the leading edge. One embodiment comprises a turbofan engine that includes a nacelle, a bypass fan, anda recirculation channel. The recirculation channel is disposed within the nacelle and has a recirculation channel inlet downstream of a leading edge of the bypass fan. The recirculation channel has one or more recirculation channel outlets upstream of the bypass fan that are proximate to a leading edge of a nacelle inlet, where the recirculation channel outlets redirect an airflow from the recirculation channel towards an inside edge of the nacelle inlet to mitigate flow separation at the leading edge of the nacelle inlet. 本发明涉及减轻机舱入口中的不利流条件。靠近涡轮风扇机舱的前缘的气流基本上正交于涡轮风扇的风扇面被喷射，从而在前缘附近产生吸力并减轻前缘附近的流分离。一个实施例包括涡轮风扇发动机，所述涡轮风扇