This paper studied the effects of suction surface corner separation on the aerodynamic performance and the effects of the blade parameters on suction surface corner separation in rectangular cascade. Corner separation alters the static pressure distribution on the suction surface, establish a C-Shape pressure distribution along spanwise, compared with open separation, closed separation intensifies the C-Shape pressure distribution, increases the streamwise adverse pressure gradient on the suction surface after the lowest pressure point. The diffusion capability in a closed separation was significantly lower than in an open separation on the separation zone, loss was larger than open separation. The changes of blade parameters have great effects on corner separation, not only affect the scale of separation zone, even they will change the separation form. This study show that with the increase of the blade thickness, the maximum thickness position moving afterwards and the increase of the deflection of mean camber line, the streamwise adverse pressure gradient on the suction surface after the lowest pressure point increase, the scale of separation zone increase, even the separation type changes from open separation to closed separation.
Numerical Investigation of Corner Separation on Compressor Cascade
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Ling, J, Du, X, Wang, S, & Wang, Z. "Numerical Investigation of Corner Separation on Compressor Cascade." Proceedings of the ASME Turbo Expo 2013: Turbine Technical Conference and Exposition. Volume 6A: Turbomachinery. San Antonio, Texas, USA. June 3–7, 2013. V06AT35A027. ASME. https://doi.org/10.1115/GT2013-95194
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