复合角对涡轮叶片旋转气膜冷却效果的影响
Numerical investigation on film cooling effectiveness of rotating blade with multihole
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摘要: 对某小型燃气轮机设计工况下的涡轮动叶,采用标准k-ε湍流模型,数值模拟了复合角气膜孔对冷却效果的影响.主流雷诺数为670 000,比较了吹风比分别为0.5,1.0,1.5和2.0时,采用60°,30,°0°,-30°和-60°复合角气膜孔的气膜流动情况和冷却效果.结果表明:在旋转状态下,压力面上复合角可以有效地提高气膜冷却效果,受哥氏力的影响,朝向低半径的复合角的气膜冷却效果要好于朝向高半径;吸力面上复合角对气膜冷却效果的影响不大.Abstract: The multihole film cooling effectiveness on rotating blade surface of an on-design turbine was numerically studied by k-ε turbulence model.Cases of 60°,30°,0°,-30°and-60° multihole were compared under different blowing ratios when the main flow Re was 670000.Results show that the rotating film cooling effectiveness can be greatly improved on pressure side with multihole,where the effectiveness of the multihole toward the low-radius is better than that of the multihole toward the high-radius because of the coriolis force.But the effectiveness isn't increased greatly on suction side with multihole.
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Key words:
- multihole /
- film cooling /
- rotating /
- blowing ratio /
- turbine
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