An air intake duct (1) for an aircraft turbine nacelle, comprising a lip (2) defining an annular cavity (24), a downstream portion (3) comprising a downstream inner wall (31) and a downstream outer wall (32), and an inner partition wall (5) separating the lip (2) from the downstream portion (3), the air intake duct (1) comprising an air delivery pipe (4) for feeding a hot air flow (Fac) into the annular cavity (24), a passage opening (51) being formed in the inner partition wall (5), an exhaust opening (34) being formed in the downstream outer wall (32), an exhaust pipe (6) is mounted in the downstream portion (3) to discharge the hot gas flow (Fac) and comprises a first end (7, 9) connected to the inner partition wall (5), a second end (8) connected to the downstream outer wall (32), and a body (61) comprising at least one flexible portion.
一种飞行器涡轮机短舱的进气管(1),包括唇缘(2)、下游部(3)以及将唇缘(2)与下游部(3)分隔的内隔壁(5),所述唇缘(2)限定出环形腔(24),下游部(3)包括下游内壁(31)和下游外壁(32),进气管(1)包括用于将热气流(Fac)送入环形腔(24)的输气管(4),通道口(51)形成于内隔壁(5),排气口(34)形成于下游外壁(32),排气管(6)安装在所述下游部(3)中以排放所述热气流(Fac)并包括与内隔壁(5)连接的第一端(7、9)、与下游外壁(32)连接的第二端(8)以及包括至少一个柔性部分的主体(61)。
Intake duct for aircraft turbine engine nacelle
飞行器涡轮发动机短舱的进气管
2022-04-08
Patent
Electronic Resource
Chinese
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |