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采用线性声学理论,将液体火箭发动机气液同轴式喷嘴分别简化为1/4波长谐振管和1/2一波长谐振管,研究得出常温条件下喷嘴长度和入口射流条件对燃烧室一阶切向声学模态的抑制规律。结果表明:当喷嘴一阶纵向模态频率与需要抑制的燃烧室声学模态频率相等时,对于喷嘴入口射流处于壅塞的状态1/4纵向模态波长长度喷嘴的抑制能力最大;反之,1/2纵向模态波长长度喷嘴的抑制能力最大。两种喷嘴的抑制能力均随喷嘴直径增加而增大。研究结果可为喷嘴长度和入口射流条件优化设计、燃烧室声学振荡抑制提供参考。
Using linear acoustic theory, the liquid-propellant rocket engine gas-liquid coaxial nozzle is simplified into a quarter-wavelength resonant tube and a half-wavelength resonant tube respectively. It is found that the length of the nozzle and the condition of the inlet jet at room temperature for the first order of the combustion chamber Suppression of tangential acoustic modes. The results show that when the first longitudinal mode frequency of the nozzle is equal to the acoustic mode frequency of the combustion chamber to be suppressed, the maximum one - quarter - longitudinal mode wavelength length nozzle can suppress the nozzle jets’ jagged state. On the contrary, 2 longitudinal mode wavelength length of the nozzle inhibition of the largest. The suppression of both nozzles increases with increasing nozzle diameter. The results can provide reference for optimal design of nozzle length and inlet jet conditions and suppression of acoustic oscillation in combustion chamber.