Abstract
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.
| Translated title of the contribution | Numerical study on matching mechanism and efficiency of pulse detonation combustor and impulse turbine |
|---|---|
| Original language | Chinese (Traditional) |
| Pages (from-to) | 1864-1871 |
| Number of pages | 8 |
| Journal | Hangkong Dongli Xuebao/Journal of Aerospace Power |
| Volume | 33 |
| Issue number | 8 |
| DOIs | |
| State | Published - 1 Aug 2018 |