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从通过激波时由于气流相对速度数值和方向的改变导致气流绝对速度和其切向分量的突跃出发,应用平面斜激波的关系,建立了△(V_θr)、损失和总压比的表达式,从理论上阐明了通过激波时气体增压这一重要现象。参考实验结果,假定通道激波的位置、形状,在进口区用特征线法,对超声速进气迴转面进行了理论分析。从这些分析可以看出跨声速压气和机的一些特点。计算还表明,在通道中线的出口处,速度矩V_θr,与中心S_z流面反问题计算时给定的数值相近;而将考虑了激波得出的V_θr,△s/R和流片厚度代入中心S_z流面计算所得的Mach数分布与常规的平均S_z计算结果在叶片排中,特别是在激波前后有很大的不同。
The relationship between △ (V_θr), loss and total pressure ratio was established by using the relationship between plane oblique shock and starting from the sudden jump of the absolute velocity and the tangential component of the airflow due to the change of the value and direction of the relative velocity of the airflow when the shock wave passes through. Type, theoretically illustrates the important phenomenon of gas pressurization through the shock wave. With reference to the experimental results, the position and shape of the channel shock wave are assumed, and the characteristic curve method is adopted in the inlet region to theoretically analyze the supersonic inlet air surface. From these analyzes, we can see some characteristics of transonic gas compressor and machine. The calculation also shows that the velocity moment V_θr at the outlet of the midline of the channel is similar to the numerical value given in the inverse problem of the flow field at the center S_z, while V_θr, Δs / R and the thickness of the flow sheet are taken into account The Mach number distribution calculated by the center S_z flow surface is very different from the conventional average S_z calculation results in the blade row, especially before and after the shock wave.