Abstract
This paper conducted preliminary numerical simulation of their interactions by means of CFD method. The stoichiometric hydrogen-air mixture was employed as reactants and 1-step finite rate reaction model was used to investigate the interaction of detonation wave with a stationary blade. The simulation results indicate that the detonation wave attenuates after passing the blade passage, and generates a strong compression wave reflecting back upstream from leading edge of blade at the same time, This mitigates the pulse effect on turbine blade and causes a short period of back mass flow at turbine inlet surface. A high pressure environment is formed at the leading edge, The pressure time sequences at pulse detonation engine (PDE) exit surface shows many pairs double-peaks are gradually attenuated.
| Original language | English |
|---|---|
| Pages (from-to) | 60-64 |
| Number of pages | 5 |
| Journal | Hangkong Dongli Xuebao/Journal of Aerospace Power |
| Volume | 24 |
| Issue number | 1 |
| State | Published - Jan 2009 |
Keywords
- Double-peaks
- Numerical simulation
- Pulse detonation engine (PDE)
- Turbine blade