Effects of Injection Scheme on Low-Frequency Oscillation in a Cavity-Based Scramjet Combustor

被引：0
|
作者：
Cui X.-D. [1 ]
Sun M.-B. [2 ]
Wang H.-B. [2 ]
Jiang X. [1 ]
Li W. [1 ]
机构：
[1] Computational Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang
[2] Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha
来源：
| 2018年 / Journal of Propulsion Technology卷 / 39期
关键词：
Cavity flameholder; Deflagration-to-detonation; Flame acceleration; Flame flashback; Injection location; Low-frequency oscillation; Thermal-acoustic instability;
D O I：
10.13675/j.cnki.tjjs.2018.10.022
中图分类号：
学科分类号：
摘要：
In order to investigate the effects of different ethylene fuel injection location upstream of a cavity flameholder on low-frequency combustion oscillation in a model engine combustor at the inflow conditions of Mach 2.52 with the stagnation temperature of 1486 K, high-frequency pressure sensor and high-speed imaging camera were used to investigate the characteristics of pressure and flame dynamics in an engine under the schemes of fuel injection close or far upstream of a cavity in a direct-connected supersonic combustion test facility with total mass flow rate of 1kg/s. The experimental results suggest that when the fuel is injected closely upstream of the cavity flameholder there exist great range of subsonic flow regions in the condition of present equivalence ratio, and low-frequency pressure oscillation which is driven by thermo-acoustic instability with a broad frequency range of 50~400Hz can occur while the amplitude of oscillation is weak. For the case that distance between the fuel injection and cavity is long, periodic flame oscillation which is charactered by flame flashback and blow-off is observed in combustor. It is suggested that long fuel injection distance is advantageous to sufficient mixing of fuel/air and produces a premixed region from the injection to the cavity, which leads to a rapid flame flashback against the incoming flow. The flame flashback is related to flame acceleration in a deflagration-to-detonation transition procedure. This process couples with the flame blow-off and a low-frequency pressure oscillation can be formed with a specific dominant frequency (about 85Hz) and strong amplitude. © 2018, Editorial Department of Journal of Propulsion Technology. All right reserved.
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页码：2370 / 2380
页数：10
相关论文
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