The invention relates to a three-flow turbine engine (10) for an aircraft, the turbine engine having a longitudinal axis (X) and comprising:-an upstream suspension member (48) located in a first plane (P1) perpendicular to the axis (X) and connected or attached to a gas generator (12) of the turbine engine; a downstream suspension member (50) located in a second plane (P2) perpendicular to the axis and connected or attached to the gas generator (12); and-a thrust absorbing rod (56) comprising a first end (56a) and an opposite second end (56b), the first end being connected or attached to the gas generator (12), the opposite second end being located in a third plane (P3) perpendicular to the axis (X), characterized in that the first, second and third planes (P1, P2, P3) are located at a cold compartment (C2) of the gas generator (12).
本发明涉及一种用于飞行器的三流涡轮发动机(10),该涡轮发动机具有纵向轴线(X)并且包括:‑上游悬挂构件(48),上游悬挂构件位于与轴线(X)垂直的第一平面(P1)中并且连接或附接到涡轮发动机的气体发生器(12);‑下游悬挂构件(50),下游悬挂构件位于与轴线垂直的第二平面(P2)中并且连接或附接到气体发生器(12);以及‑推力吸收杆(56),推力吸收杆包括第一端部(56a)和相对的第二端部(56b),第一端部连接或附接到气体发生器(12),相对的第二端部位于与轴线(X)垂直的第三平面(P3)中,其特征在于,第一平面、第二平面和第三平面(P1,P2,P3)位于气体发生器(12)的冷隔室(C2)处。
Suspension of three-flow aircraft turbine engine
三流飞行器涡轮发动机的悬挂
2024-11-19
Patent
Electronic Resource
Chinese