旋转对涡轮叶片异型孔气膜冷却的影响

发布时间：2018-02-26 20:03

本文关键词： 涡轮叶片异型孔气膜冷却旋转雷诺数数值模拟　出处：《推进技术》2016年09期 　论文类型：期刊论文

【摘要】：为了揭示异型气膜孔在旋转状态下的冷却特性,采用数值模拟的方法分析了吹风比为0.6时旋转对涡轮叶片异型气膜孔流动及冷却的影响,包括三种气膜孔:圆孔、扇形孔及收敛缝型孔。结果表明:旋转时气膜射流受离心力和哥氏力作用朝叶尖方向偏转,射流涡结构被弱化而变得不明显,气膜射流向主流的穿透得到一定程度的削弱;圆孔和扇形孔冷却效率随旋转雷诺数增大而升高,局部最多可分别提高100%和50%左右,收敛缝型孔冷却效率受旋转雷诺数的影响较小;旋转状态下扇形孔冷却效果与收敛缝型孔相当,仍然优于圆孔。
[Abstract]:In order to reveal the cooling characteristics of special-shaped gas film holes in rotating state, the effect of rotation on the flow and cooling of irregular film holes in turbine blades when the blowing ratio is 0.6 is analyzed by numerical simulation, including three kinds of gas film holes: circular holes. The results show that the film jet deflects towards the tip of the blade under the action of centrifugal force and Coriolis force, the vortex structure of the jet is weakened, and the penetration of the film jet to the main stream is weakened to a certain extent. The cooling efficiency of circular and sector holes increases with the increase of rotary Reynolds number, and the local maximum increases by about 100% and 50%, respectively. The cooling efficiency of convergent slot holes is less affected by rotary Reynolds number. The cooling effect of sector hole in rotating state is equal to that of convergent slot hole and is still superior to that of round hole.
【作者单位】：南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室;
【基金】：国家自然科学基金(U1508212) 江苏省研究生培养创新工程(KYLX_0307) 中央高校基本科研业务费专项资金江苏省航空动力系统重点实验室开放课题(NJ20130026)
【分类号】：V231.1

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