摘要
研究了驱动压力脉动频率对脉动燃烧器冷态压力脉动特性的影响，还研究了驱动压力脉动和温度脉动的相位差对燃烧器系统的压力脉动特性的影响。频谱图表明，f≈（1＋m）fd（有时f=（+m）fd处，都出现压力脉动的峰值）。f≈（1＋m）fd≈（1＋n）f0时压力脉动的幅值大于f=（1＋m）fd≈（1／2＋n）f0或f=（1／2＋m）fd≈（1／2＋n）f0的幅值。当驱动压力脉动和温度脉动频率相同相位相近时，脉动燃烧加剧，随着相位差增加，燃烧器系统压力脉动减弱。如果驱动压力脉动幅值足够大，到一定的相位差时，脉动燃烧停止工作。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 effect of frequencies of an exciting pressure pulsation as well as the phase difference between the exciting pressure and the temperature pulsations on the characteristics of the pressure pulsation in a pulse combustor is inverstigated. The spectrum shows that amplitude peaks of pressure pulsation exist at f≈ (1+m )fd or sometimes at f= (+m )fd. The amplitude peaks of pressure oscillation at f= (1 +m ) fd≈(1 +n)f0 are greater than that of pressure oscillation at f= (1 +m )fd≈ (1/2 +n)f0 or f= (1/2 +m )fd≈ (1/2 +n)f0. It is shown that the pulse combustion becomes serious when the phase difference between the exciting pressure and the temperature pulsations is decreased. The pulse flame will be blowout at certain phase difference, if the amplitude of the exciting pressure pulsation is great enough.The above experimental result is of value for the mechanism and suppression of low frequency combustion oscillation in an afterburner of a turbofan engine.
出处
《南京航空航天大学学报》
EI
CAS
CSCD
北大核心
1997年第1期96-101,共6页
Journal of Nanjing University of Aeronautics & Astronautics
关键词
加力燃烧室
脉动燃烧
振荡燃烧
航空发动机
afterburners
combustion instability
combustion oscillation
pressure fluctuation
