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以某型航空发动机燃烧室为物理模型,改进了计算火焰筒流量分配的流阻法,并对其进行验证,结果冷却空气量的相对误差为5.7%;采用多项式拟合法计算了火焰筒燃气总温沿轴向分布,得到了主燃区总温和燃烧室出口总温,并采用燃烧效率法对其进行了验证,二者的相对误差分别为4.4%和1%。结果表明:在初始设计阶段,采用改进的流阻法和多项式拟合法验证火焰筒的沿程空气流量分配和沿程燃气总温合理有效。
Based on the physical model of a certain type of aeroengine combustor, the flow resistance method for calculating the distribution of the flame tube is improved and verified. The relative error of the amount of cooling air is 5.7%. The polynomial fitting method is used to calculate the total gas Temperature distribution in the axial direction, the total temperature of the main combustion zone and the total temperature of the outlet of the combustion chamber were obtained, and the combustion efficiency method was used to verify the results. The relative errors between the two were 4.4% and 1% respectively. The results show that in the initial design stage, the improved flow resistance method and polynomial fitting method are used to verify the distribution of the air flow along the flame tube and the total temperature of the gas along the pipeline are reasonable and effective.