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根据实验测量的脉冲爆震燃烧室壁温沿程分布,推算出符合脉冲爆震燃烧室特定频率下的准稳态热流阶梯分布;在此基础上,针对叉排阵列射流冲击冷却的脉冲爆震燃烧室壁面温度分布进行了数值计算.研究表明,由于冷却气流通道端壁效应的影响,靠近爆震燃烧室尾部的射流孔的冲击射流速度较大,热流最大的燃烧室尾部管壁的温度可以得到有效的降低,而燃烧室中部的射流由于受到前排射流形成的横流影响,对管壁的冲击冷却效果较弱,使得壁面温度的峰值向中部转移.在相同的环形冷却通道进口雷诺数下,阵列射流孔宜布置在脉冲爆震燃烧室中部,射流冲击间距比Zn/d=1.5时,管壁的峰值温度最低而且整体的平均温度最小,较小的冲击孔直径对应的冲击冷却效果较好.
Based on the experimentally measured distribution of wall temperature along the pulse detonation chamber, the quasi-steady heat flow ladder distribution is calculated to meet the specific frequency of the pulse detonation combustor. Based on this, the pulse detonation The results show that due to the influence of the endwall effect of the cooling air flow channel, the impact jet velocity of the jet hole close to the tail of the knocking combustion chamber is relatively large, and the temperature of the tail pipe wall with the largest heat flux can be And the jet flow in the middle of the combustion chamber is impacted by the cross flow formed by the front jet and the impact cooling effect on the tube wall is weak so that the peak value of the wall temperature shifts to the middle.Under the same inlet recirculation of the annular cooling channel , The array of jet holes should be arranged in the middle of the pulse detonation combustor. When the jet impact pitch ratio Zn / d = 1.5, the peak temperature of the tube wall is the lowest and the overall average temperature is the smallest. The impact cooling effect corresponding to the smaller hole diameter is smaller it is good.