摘要
As the turbine inlet was dominated by strong unsteady airflow when working with the pulse detonation combustor (PDC), the type of turbine was determined based on the loss mechanism and the aerodynamic design work of turbine components was carried out. The numerical method was used to calculate the efficiency of the designed turbine and explore the mechanism of the interaction between the PDC and the turbine. The results showed that partial intake, impulse turbine with less reaction degree was more suitable for PDC; a strong reflection shock wave was formed on the contraction section of nozzle, the leading edge and the pressure surface of the rotor blade, which cause energy loss; the efficiency of turbine was about 75% at the design point. The results can provide some reference for turbine design of pulse detonation turbine engine.
| 投稿的翻译标题 | Numerical study on matching mechanism and efficiency of pulse detonation combustor and impulse turbine |
|---|---|
| 源语言 | 繁体中文 |
| 页（从-至） | 1864-1871 |
| 页数 | 8 |
| 期刊 | Hangkong Dongli Xuebao/Journal of Aerospace Power |
| 卷 | 33 |
| 期 | 8 |
| DOI | |
| 出版状态 | 已出版 - 1 8月 2018 |
关键词
- Aerodynamic design
- Impulse turbine
- Matching mechanism
- Pulse detonation combustor(PDC)
- Turbine efficiency