非定常尾迹对叶片头部气膜冷却的影响
The Effect of Unsteady Wake on Leading Edge Film Cooling
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摘要: 采用数值模拟的方法分析了非定常尾迹对叶片头部气膜冷却的影响,气膜冷却方式为狭缝冷却。将数值模拟得到的气膜冷却有效温比同相应的实验结果进行了比较,用来校验程序。通过对数值模拟的结果进行分析,发现当非定常尾迹作用到叶片头部时,主流的滞止点会从气膜狭缝上游移动到气膜狭缝上,气膜射流会发生“分流”现象,导致气膜狭缝下游壁面的气膜冷却有效温比急剧下降。Abstract: Numerical simulations were performed to study the affect of unsteady wake on leading edge film cooling.The calculated film cooling effectiveness was compared with the experimental results.The unsteady numerical simulation shows that the stagnation point moving to the cooling flow slit causes the cooling flow to diverge when the unsteady wake swept through the film-cooling slit.The divergence of the cooling flow results in sharply decreasing of the film cooling effectiveness downstream the film-cooling slit.
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Key words:
- aerospace propulsion system /
- unsteady wake /
- film cooling /
- film cooling effectiveness
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