摘要
Based on component matching and multi-point analysis, a turbofan plus lift fan engine performance simulation model was developed. The model was tested by the F135 engine. The simulation results show that the engine performance is the same as the conventional turbofan in cruise mode. When the lift fan is engaged, the matching point between the low pressure turbine, the cruise fan and the lift fan is achieved by adjusting the nozzle throat area, the bypass exit area, and the low pressure turbine throat area. Based on this model, the cycle parameter matching and performance analysis can be achieved for the turbofan plus lift fan engine in different missions.
| 源语言 | 英语 |
|---|---|
| 页（从-至） | 1095-1100 |
| 页数 | 6 |
| 期刊 | Hangkong Dongli Xuebao/Journal of Aerospace Power |
| 卷 | 28 |
| 期 | 5 |
| 出版状态 | 已出版 - 5月 2013 |