Influence of Key Profile Geometric Parameters on Supersonic Cascade Performance
Supersonic profiles are widely used in aviation compressors,and its key geometric parameters have an important impact on their aerodynamic performance.This paper aimed at inlet Mach number of 1.4,studies the influence of the maximum thickness,maximum deflection and cascade consistency on the aerodynamic performance of supersonic airfoil by the numerical calculation method of flow field.The results show that the variation of the maximum thickness and the maximum deflection has little effect on the shock structure in the cascade channel.With the decrease of the maximum thickness,the static pressure ratio corresponding to the minimum loss increases and the back pressure resistance increases,which is conducive to achieving higher pressure ratio design.And with the decrease of the maximum deflection,the back pressure resistance of the cascade decreases and the minimum loss remains almost unchanged,which is adverse to the design of the high pressure ratio.Increasing the consistency will cause the channel shock wave to shift to the upstream of the cascade channel until the detached shock wave is formed,which will increase the loss of the cascade under all operating conditions.
supersonic profilekey geometric parametersshock wave structureflow field performanc
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