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Experimental Investigation into the Effects of Riblets on Compressor CascadePerformance

机译：“沟槽”对压缩机叶栅性能影响的试验研究

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The effects of adding riblets to the blades of a subsonic, linear compressorcascade were investigated at the Air Force Institute of Technology. Three blade configurations were tested, including a set of unmodified NACA 64-A905 series blades, a set with riblets applied to the suction surface, and a set with riblets on the pressure surface. Performance was evaluated over a wide range of Reynolds numbers, and at low and high free stream turbulence levels. Cascade performance was evaluated in terms of total pressure loss coefficient, turning angle, and static pressure rise. No riblet configuration offered robust cascade performance improvements; however, performance was significantly enhanced under certain specific conditions. Riblets also degraded cascade performance at other conditions.

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Rothenflue, J. A.;
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年度 1991
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总页数 137
原文格式 PDF
正文语种 eng
中图分类工业技术;
关键词
Air force; Angles; Blades; Coefficients; Compressors; Losses; Performance(Engineering); Pressure; Pressure gradients; Range(Extremes); Reynolds number; Static pressure; Subsonic characteristics; Suction; Surfaces;

机译：空军;角度;叶片;系数;压缩机;损失;性能（工程）;压力;压力梯度;范围（极值）;雷诺数;静压;亚音速特性;吸力;表面;

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Experimental Investigation into the Effects of Riblets on Compressor CascadePerformance

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