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通过对某航空发动机试车间的进气流场特性进行数值模拟研究,得出发动机试车间的进气流场流动特性,分析了流量测量误差随测量截面及探针深入位置的变化规律,并针对特定截面和深入位置,研究了边界层厚度随不同马赫数和不同雷诺数的变化规律,最后对工程中的流量系数测量方法做了系统性分析。结果表明,随测量截面向发动机进气口的推移,附面层越来越薄,压力测点越向中心区分布,测量速度越来越接近截面的平均速度;马赫数对流量系数的影响很小,流量系数随着雷诺数的增大而增大。
Through the numerical simulation study of the inlet flow field characteristics of an aeroengine test shop, the flow characteristics of the inlet flow field in the engine test workshop are obtained. The variation of the flow measurement error with the measurement cross section and probe depth is analyzed. Specific section and in-depth position, the variation law of boundary layer thickness with different Mach number and different Reynolds number was studied. Finally, the systematic analysis of the flow coefficient measurement method in engineering was made. The results show that with the passage of the measurement cross section to the engine inlet, the thickness of the coating becomes thinner and the pressure measurement points are more distributed to the central area, and the measurement speed is closer to the average velocity of the cross section. The influence of the Mach number on the flow coefficient is very small Small, flow coefficient increases with increasing Reynolds number.