空气涡轮火箭发动机风车状态数值仿真研究

Numerical simulation of air turbo rocket engine at windmilling state

开展了飞行高度20 km、速度Ma 3条件下,空气涡轮火箭发动机(ATR)风车状态数值仿真研究。根据ATR发动机结构方案,建立了三维计算模型,并以压气机转子扭矩为0作为风车状态判据,使用计算流体动力学方法,计算获得了不同给定转速下ATR发动机三维流场结果。研究发现,冷态条件下随着给定压气机转子转速的不断升高,发动机通流能力逐渐增强,发动机入口气流静压逐渐降低,速度逐渐增加。同时,确认了在飞行高度20 km、速度Ma 3条件下,ATR发动机风车转速约为6 900 r/min,内阻约2 170 N。此时,发动机进出口总压损失约61%。其中,压气机流道进出口总压损失达到了32.6%。

Under the flight condition that is flight altitude 20 km and mach number 3, numerical simulation of Air Turbo Rocket engine(ATR) at windmilling state is presented in the paper. Based on the structure of ATR, the 3-D numerical model is established, and the flowfield at different appointed revs is obtained by using the method of computational fluid dynamics. It's found that static pressure decreases and the velocity increases at the entrance of ATR as the revs of compressor rotor increases.Meanwhile taking that the value of torque is zero as the criterion of windmilling state, it is confirmed that under the given flight condition the revs of ATR at windmilling state is about 6 900 r/min, and the internal drag is about 2 170 N.And the total pressure loss is about 61% all through the engine.Through the compressor, the total pressure loss reaches about 32.6%.