The invention relates to an air intake (3) for a nacelle (1) of an aircraft engine (6), the air intake (3) comprising a front lip (31) connecting a substantially cylindrical internal wall (32) and a substantially cylindrical external wall (33), a front mounting flange (34) configured to collaborate with a rear flange (44) of a wall of the turbine engine, the air intake being characterized in that it exhibits a support structure (50) extending from a lower end configured to be secured to a fan casing (42) at the level of the rear flange (44), as far as an upper end in contact with at least a downstream part of the external wall (33) of the air intake (3), said support structure (50) comprising access openings (70) configured to have maintenance tools passed through them during maintenance operations on the air intake (3).
本发明涉及一种用于飞行器发动机(6)的短舱(1)的进气道(3),所述进气道(3)包括连接大致圆柱形内壁(32)和大致圆柱形外壁(33)的前边缘(31),被配置成与涡轮发动机的壁的后凸缘(44)配合的前安装凸缘(34),所述进气道的特征在于,其具有支撑结构(50),所述支撑结构从被配置成在后凸缘(44)处固定到风扇壳体(42)的下端延伸,直到与进气道(3)的外壁(33)的至少下游部分接触的上端,所述支撑结构(50)包括检修孔(70),所述检修孔被配置成在对进气道(3)进行维护操作期间由维护工具穿过。
NACELLE AIR INTAKE AND NACELLE COMPRISING SUCH AN AIR INTAKE
短舱进气道和包括这种进气道的短舱
2021-11-30
Patent
Elektronische Ressource
Chinesisch
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