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本文给出了一种基于区域分解算法的可考虑动叶顶部间隙和机匣刮削作用的涡轮级计算方法。并对NASA实验涡轮级进行了计算 ,计算结果和实验结果吻合得很好。通过分析 ,可以发现动叶顶部间隙流动将引起动叶顶部气流的欠偏转 ,从而降低顶部的做功能力 ,并且这一影响区域会达到一个相当大的范围。在动叶叶片顶部尾缘存在激波的情况下 ,尾缘激波和顶部泄漏流动相互作用使激波结构变得十分复杂和无序 ,这种无序的结构必然带来较大的损失。
In this paper, a turbine-based method based on the regional decomposition algorithm is proposed, which can consider the top clearance of the rotor blades and the scraping effect of the casing. The NASA experimental turbine stage is calculated. The calculated results are in good agreement with the experimental results. Through the analysis, it can be found that the clearance flow at the top of the moving blade will cause the deflected airflow at the top of the moving blade, so as to reduce the workability of the top and reach a considerable area in this area of influence. Under the condition that there is a shock wave at the top trailing edge of the rotor blade, the interaction between the trailing edge shock wave and the top leakage flow causes the shock structure to become very complicated and disorderly, and this disordered structure inevitably brings greater losses.