涡扇发动机起动过程气动稳定性的数值计算

Computation and assessment of aerodynamic stability of turbofan engine startup and acceleration

基于燃气涡轮发动机部件匹配原理,发展了数值计算涡扇发动机起动过程气动稳定性的一维数学模型和软件。以某型涡扇发动机为例,计算分析了不同的起动方式、飞行条件对发动机气动稳定性和燃烧室燃烧稳定性的影响。从计算结果和与试验数据的对比可以看出,发展的计算涡扇发动机起动过程气动稳定性的数学模型和方法,给出的起动过程发动机共同工作线走向和燃烧室稳定性判断标准是合理的。

Based on component matching principles and by through solving unsteady state continuum equation, momentum equation and energy equation, one dimensional mathematical model was developed for aerodynamic stability assessment of turbofan engine startup and acceleration. With this model, aerodynamic stability of startup of small turbofan engine for missile was simulated. Effects of startup method and flight conditions on aerodynamic stability of turbofan engine startup and acceleration were given. According to model results and comparison with flight test data, it is found that the model developed could be used to compute aerodynamic stability during turbofan engine startup.