二维无旋超音速扩散对称流动控制方程及其特征线方程和相容性方程

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通过改变止推气体轴承等间隙的流道结构,对变气膜厚度圆盘止推气体轴承中二维无旋超音速扩散对称流动控制方程进行推导,得出其特征线方程和相容性方程,对所得特征线方程和相容性方程用等间隙气膜内一维超音速流动的解析解进行验算。结果表明,当内点间距合适时,特征线法数值求解与解析解结果十分接近,推导的特征线方程和相容性方程正确。 By changing the flow structure of the clearance of the aerostatic thrust bearing,this paper deduces the control equation for the 2D diffusion irrotational supersonic symmetry flow in the circular aerostatic thrust bearing of variable film thickness,based on which the characteristic line equation and compatibility equation are further derived.The analytic solution of 1D supersonic flow in the gas film of equal clearance is used to verify the characteristic line equation and compatibility equation.The results show that,when interior point spacing is appropriate,the results of the characteristic numerical method is very close to those of the analytical solution,and the characteristic line equation and compatibility equation are correct.