タービン翼列の遷音速特性予測に関する研究

概要

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Transosic characteristics of three similar turbine cascades (designed for same condition, but with slightly different curvature of blade suction surface after throat) were tested by high-speed cascade wind tunnel. Experimental data showed small difference of curvature of blade suction surface after throat affected loss coefficient in transonic region. Only one cascade with straight suction surface after throat showed additional loss in the region of outlet Mach number near unity. Numerical simulation using Compressible Navier-Stokes TVD scheme was applied to these cascades. Computed loss characteristics were very similar to experimental results. The computed Mach number distribution showed the correlation between the difference of loss coefficient and the difference of the strength of shock wave from the wake of cascades. There was also difference of boundary layer growth on the suction surface after throat in two types of cascades, one had additional loss and others didn't.
一般社団法人日本機械学会の論文
1998-12-25