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针对涡轮导向叶片吸力面和压力面上特定位置上的单排气膜孔,在吹风比为0.44～2.67范围内,数值研究非对称扇形气膜孔的冷却特性。基准对称扇形孔侧向扩展角为20°,后向扩展角为10°。研究结果表明,在扇形总扩展角相等的条件下,非对称型扇形气膜孔的气膜出流穿透能力与对称型扇形气膜孔基本相当,但气膜出流侧向覆盖范围较对称型扇形气膜孔有一定程度的改善,在高吹风比下扇形气膜孔侧向扩展角的影响较为显著。相对而言,非对称扇形气膜孔改善气膜冷却的效果在涡轮叶片压力面侧能得到更好的体现。
Aiming at the single-row film holes on the suction side and the pressure side of the turbine guide vane, the cooling characteristics of asymmetrical fan-shaped film holes were numerically studied in the range of 0.44 ~ 2.67. The symmetrical fan-shaped hole has a lateral expansion angle of 20 ° and a backward expansion angle of 10 °. The results show that under the condition of equal fan-shaped total expansion angle, the outflow penetrating ability of the asymmetrical fan-shaped film holes is almost the same as that of the symmetrical fan-shaped film film holes, but the lateral coverage of the outflow film is symmetrical Type fan-shaped film hole to some extent improved, the fan-shaped film hole lateral expansion angle under high blowing ratio is more significant. Relatively speaking, the effect of asymmetrical fan-shaped film hole to improve the film cooling can be better reflected on the pressure side of the turbine blade.