A system (34) for controlling the pitch setting of propeller blades (10) of an aircraft turbine engine is disclosed, characterized in that the system comprises:-a blade (10) comprising a blade (12) connected to a root (14); -a cup (58) comprising an annular wall (58a) extending around the pitch axis (A) of the vane (10) and a lower axial end closed by a bottom wall (58b); -a fixing ring (52) extending around the root (14) and located within the cup (58); the system further comprises a security element (110, 110 ') ensuring the retention of the root (14) with the cup (58), said at least one security element (110, 110') having a substantially elongated shape and passing through an alignment hole (112, 114, 126) in the bottom wall (58b) of the cup (58) and in the free end (28) of the root (14).
公开了一种用于对飞行器涡轮发动机的螺旋桨轮叶(10)的节距设定进行控制的系统(34),其特征在于,该系统包括:‑轮叶(10),该轮叶包括连接到根部(14)的叶片(12);‑杯状部(58),该杯状部包括围绕轮叶(10)的节距轴线(A)延伸的环形壁(58a)和由底壁(58b)封闭的下轴向端部;‑固定环(52),该固定环围绕根部(14)延伸并且位于杯状部(58)内;该系统还包括安全元件(110,110’),该安全元件确保根部(14)与杯状部(58)的保持,所述至少一个安全元件(110,110’)具有大致细长的形状,并且穿过杯状部(58)的底壁(58b)以及根部(14)的自由端部(28)中的对准孔(112,114,126)。
System for controlling pitch setting of propeller blades of aircraft turbine engine
用于对飞行器涡轮发动机的螺旋桨轮叶的节距设定进行控制的系统
2023-04-18
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
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