Helmholtz resonators and quarter wave resonators are studied as the high frequency combustion instabilities suppression devices in liquid rocket engines.
本文针对抑制液体火箭发动机不稳定燃烧的声学装置——赫姆·霍兹声腔和四分之一波长管声腔进行了研究。
The above experimental result is of value for the mechanism and suppression of low frequency combustion oscillation in an afterburner of a turbofan engine.
上述结果对研究低频振荡燃烧机理和抑制技术有一定的参考价值。
The experimental system is set up for combustion explosion and explosion suppression of in-pipe combustible gas. The testing response time of the system is less than 0.001s.
建立了管内可燃气体燃烧爆炸和爆炸抑制的试验研究系统，该系统测试响应时间小于0.001秒，测量精度为0.5%。
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