Journal
PROCEEDINGS OF THE COMBUSTION INSTITUTE
Volume 35, Issue -, Pages 2137-2144Publisher
ELSEVIER SCIENCE INC
DOI: 10.1016/j.proci.2014.09.005
Keywords
Supersonic combustion; Low frequency oscillation; Mixing; Cavity flameholder
Funding
- National Natural Science Foundation of China [91116001, 91016028]
- Fok Ying Tung Education Foundation [131055]
- Education Ministry of China
Ask authors/readers for more resources
The present work investigated combustion instabilities inside an ethylene-fueled scramjet combustor mounted on a Mach 2.1 direct-connect test facility with an inflow stagnation temperature of 846 K. Effects of fueling schemes on the combustion stability characteristics were examined. The experimental results suggest that the oscillation modes correlate with mixing status closely. For the cases with a quasi-steady thermal throat or stable shock trains, flame fluctuation exists in a mode of thermo-acoustic type oscillation with a broad frequency range. For the cases with a transient thermal throat, if a fuel/air premixed region from the injection to the cavity flameholder exists, the cavity pilot flame could reignite the fuel/air mixture and undergo a process similar to deflagration-detonation transition (DDT). This process couples with the flame quenching upstream of the injection location, and a DDT-type low frequency oscillation can be formed. (C) 2014 The Combustion Institute. Published by Elsevier Inc. All rights reserved.
Authors
I am an author on this paper
Click your name to claim this paper and add it to your profile.
Reviews
Recommended
No Data Available