Abstract
The interdependence between flame stabilization modes and the combustion modes in an ethylene-fueled supersonic combustor was characterized. The flame stabilization modes were systematically mapped as a function of the fuel global equivalence ratio and the stagnation temperature. The boundaries of different modes shifted to the higher global equivalence ratio as increasing the stagnation temperature increased the flow velocity. The flame was stabilized in cavity shear layer when the combustor operated in a scramjet mode; that in jet-wake when the combustor operates in a ram- jet mode.
| Original language | English |
|---|---|
| Pages (from-to) | 2919-2925 |
| Number of pages | 7 |
| Journal | Proceedings of the Combustion Institute |
| Volume | 36 |
| Issue number | 2 |
| DOIs | |
| Publication status | Published - 1 Jan 2017 |
Keywords
- CH∗ chemiluminesence
- Flame stabilization
- Gloabal equivalence ratio
- Stagtnation temperature
- Supersonic combustion
ASJC Scopus subject areas
- Chemical Engineering(all)
- Mechanical Engineering
- Physical and Theoretical Chemistry