The invention discloses an aero-engine nacelle and an aero-engine. The aero-engine nacelle comprises an air inlet channel, a fan casing and a reinforcing rib, the air inlet channel comprises a lip, the fan casing is connected to the axial rear side of the air inlet channel, the reinforcing rib is arranged on the outer wall of the air inlet channel and the outer wall of the fan casing and extends in the axial direction, an air supply channel for hot air to flow is formed in an inner cavity of the reinforcing rib, and hot air flows to the lip through the air supply channel. According to the aero-engine nacelle, an air supply channel is formed by the inner cavities of the reinforcing ribs arranged on the outer walls of the air inlet channel and the fan casing, so that the surface of the lip is prevented from being frozen. And parts such as an air supply pipeline specially used for supplying hot air are omitted, so that the maintainability of the nacelle is improved.
本发明公开了一种航空发动机短舱和航空发动机。航空发动机短舱包括进气道、风扇机匣和加强筋,进气道包括唇口,风扇机匣连接于进气道的轴向后侧,加强筋设置于进气道和风扇机匣的外壁上且沿轴向延伸,且加强筋的内腔形成供热气流动的供气通道,热气通过供气通道流动至唇口。本发明的航空发动机短舱利用进气道和风扇机匣的外壁上设置的加强筋的内腔来形成供气通道,以防止唇口表面结冰。且省去专门用于供送热空气的供气管路等零件,从而提高了短舱的维护性。
Aero-engine nacelle and aero-engine
航空发动机短舱和航空发动机
2022-07-29
Patent
Elektronische Ressource
Chinesisch
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
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