双转子涡喷发动机气动性能优化控制研究

航空发动机的控制规律作用巨大，它决定了发动机能否获得设定的稳态工作下性能指标，同时保证工作过程中的压气机和涡轮的气动稳定性。双转子涡喷发动机气动性能优化控制的目的就是有效地挖掘发动机的使用潜力。研究方法采用部件特性法对发动机进行稳态建模，并针对某双转子涡喷发动机的稳态模型进行三种不同稳态控制规律下的仿真，得到发动机性能参数的不同变化趋势，并对其进行了详细的分析。结果表明：保持低压转子转速不变的情况下，随着压气机进口总温的增加，高压转子转速上升，涡轮前温度升高，发动机推力增加；保持涡轮前温度不变的情况下，随着压气机进口总温的升高，低压压气机气动负荷变重，低压转子转速降低；高压转子转速也下降，但是下降幅度很小；燃油流量增加；保持高压转子转速不变的情况下，随着压气机进口总温的升高，燃油流量有一定的增加，低压转子转速有所降低；推力受多重因素的影响，推力值变化趋势较为复杂。

Study on aerodynamic performance optimization control of twin rotor turbojet engine

Whether the aero engine can obtain the steady state performance, at the same time ensure the stability of the working process, to a large extent, depends on the control law of the engine. The aerodynamic performance optimization control can effectively excavate the potential of the engine. Component characteristics method was adopted for static modeling of the engine, and conducts simulation of steady state under three different control laws for a twin rotor turbojet engine, gets change trend of different engine performance parameters, then detailed analysis was carried on. The results show that under control law of keep low pressure rotor speed unchanged, with the increase of compressor inlet total temperature, the speed of the high pressure rotor is increased, the temperature of turbine inlet is increased and the thrust of the engine is increased; Under control law of keep the temperature of turbine inlet unchanged, with the increase of compressor inlet total temperature, low pressure compressor load becomes heavier, the low pressure rotor speed is decreased, the high pressure rotor speed is also decreased, but the drop is very small, and the fuel flow rate increases; Under control law of keep high pressure rotor speed unchanged, with the increase of the total temperature of compressor inlet, the fuel flow rate increases, the low pressure rotor speed decreases, engine thrust is influenced by multiple factors, so the thrust value change trend is more complicated.