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根据喷嘴长度和入口边界条件,将液体火箭发动机气液同轴式喷嘴简化为4类:四分之一波长闭管、二分之一波长闭管、四分之一波长开管和二分之一波长开管。采用线性声学理论对喷嘴入口开口率的声学抑制影响进行了研究,得到了入口开口率声学影响规律。结果表明:在标准长度和最佳长度2种条件下,开口率对喷嘴抑制能力的影响差别很大。合理选择开口率和喷嘴长度能够有效提高喷嘴抑制能力。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。
According to the nozzle length and inlet boundary conditions, the liquid rocket engine gas-liquid coaxial nozzle is simplified into four categories: quarter-wave closed tube, half-wave closed tube, quarter-wave open tube and half A wavelength of open tube. The linear acoustic theory was used to study the influence of acoustic suppression on the nozzle opening ratio. The acoustic influence of the inlet opening ratio was obtained. The results show that the aperture ratio has a great influence on the suppression ability of the nozzle under both the standard length and the optimal length. A reasonable choice of aperture ratio and nozzle length can effectively improve the nozzle suppression ability. The results can provide reference for optimal design of nozzle length and inlet jet conditions and suppression of acoustic oscillation in combustion chamber.