变几何涡轮叶栅叶端小翼的气动性能
收稿日期: 2015-12-17
修回日期: 2016-04-29
网络出版日期: 2016-05-04
基金资助
国家自然科学基金（51406039）；黑龙江省自然科学基金（QC2016059）
Aerodynamic performance of a variable geometry turbine cascade using a vane-end winglet
Received date: 2015-12-17
Revised date: 2016-04-29
Online published: 2016-05-04
Supported by
National Natural Science Foundation of China (51406039); Natural Science Foundation of Heilongjiang Province of China (QC2016059)
针对大子午扩张变几何涡轮在可调静叶转动时旋转轴端严重恶化端区流场的问题，提出在可调静叶的机匣端部应用小翼结构的方法以克服这一问题并减少叶端间隙泄漏流动。应用数值方法和标准k-ω两方程湍流模型，并结合低速风洞试验，首先研究了可调静叶栅小翼端部流场及损失分布，并考虑了可调静叶转动的影响，随后给出了叶端凹槽状小翼结构，并评估了其气动性能以及对间隙变化的敏感性。研究结果表明：在可调静叶栅中应用叶端小翼不但可以避免可调静叶转动时旋转轴端恶化端区流场，还降低了叶端间隙泄漏驱动力，从而使得可调静叶在所有转角下都具有较好的端区流动性能，并且叶端小翼结合凹槽结构可以进一步减少间隙泄漏，总体上可调静叶栅总压损失系数降低了8.9%。
高杰 , 郑群 , 刘鹏飞 , 魏明 . 变几何涡轮叶栅叶端小翼的气动性能[J]. 航空学报, 2016 , 37(12) : 3615 -3624 . DOI: 10.7527/S1000-6893.2016.0139
In a high endwall-angle variable-geometry turbine, the rotating shaft end can lead to a serious deterioration of endwall flow fields when the variable vane rotates. A winglet is proposed to be applied to the variable vane casing-end to overcome this problem and then reduce the vane-end leakage flow. Combined with the low-speed wind tunnel test, numerical investigation is performed by solving Reynolds-averaged Navier-Stokes equations in conjunction with a standard k-ω two-equation turbulence model. The endwall flow fields and loss distribution of the variable vane with winglets are analyzed. The effects of vane turning are discussed. The vane-end cavity-winglet structure is then proposed, and the aerodynamic performance and its sensitivity to vane-end clearance height are evaluated. The results show that the variable vane with winglets can not only avoid the deterioration of endwall flow fields caused by vane turning, but also reduce the vane-end clearance leakage driving force, thus leading to improved endwall flow performance of variable vanes at all turning angles. Besides, the variable vane with cavity-winglets can further reduce the leakage flow, and the total pressure loss coefficient is reduced overall by 8.9% as compared to the baseline.
Key words： variable geometry turbine; winglet tip; cavity tip; aerodynamic loss; cascade
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