IMECH-IR  > 高温气体动力学国家重点实验室
Experimental study of combustion oscillations in a dual-mode scramjet
Tian XD; Chen LH(陈立红); Gu HB(顾洪斌); Liu C; Cheng LW; Chang XY(张新宇); Chen, Lihong (lhchen@imech.ac.cn)
2015
Conference Name20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015
Conference Date2015
Abstract

Characteristics of combustion oscillations were studied experimentally in a direct-connected supersonic combustion test facility with a cavity flameholder and transverse fuel injection from the wall. Static pressures were obtained by using high-frequency dynamic pressure transducers. The effects of inlet Mach number and fuel injection were examined. The frequency spectrum of wall pressures shows that combustion oscillations are different between the ramjet mode and the scramjet mode. In the ramjet mode, the high frequency combustion oscillations are on the same order of frequency as cavity oscillations. The low frequencies increase as inlet Mach number increase and fall in a range of 200-450Hz. In the scramjet mode, the high frequency combustion oscillations exist in trailing edge of the cavity, the frequencies are about 4 kHz and the occurrence is related with transverse injection momentum ratio. © 2015, AIAA American Institute of Aeronautics and Astronautics. All rights reserved.

ISBN9781624103209
Indexed ByEI
Language英语
Document Type会议论文
Identifierhttp://dspace.imech.ac.cn/handle/311007/60702
Collection高温气体动力学国家重点实验室
Corresponding AuthorChen, Lihong (lhchen@imech.ac.cn)
Recommended Citation
GB/T 7714
Tian XD,Chen LH,Gu HB,et al. Experimental study of combustion oscillations in a dual-mode scramjet[C],2015.
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