摘要
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.
| 源语言 | 英语 |
|---|---|
| 页（从-至） | 221-224 |
| 页数 | 4 |
| 期刊 | Tuijin Jishu/Journal of Propulsion Technology |
| 卷 | 27 |
| 期 | 3 |
| 出版状态 | 已出版 - 6月 2006 |