涡轮转子叶片异型气膜孔冷却数值研究

朱兴丹; 张靖周; 谭晓茗; 郭文; 苏云亮

doi:10.13224/j.cnki.jasp.2016.09.003

涡轮转子叶片异型气膜孔冷却数值研究

doi: 10.13224/j.cnki.jasp.2016.09.003

1. 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, 南京 210016;
2. 中国航空工业集团公司中国燃气涡轮研究院, 成都 610500

基金项目:

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；航空科学基金（2015ZB52019）

详细信息

作者简介:
朱兴丹(1989-),男,江苏海门人,博士生,主要从事航空发动机热端部件冷却技术研究.

中图分类号: V231.1
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出版历程
- 收稿日期: 2015-01-07
- 刊出日期: 2016-09-28

Numerical investigation of shaped-hole film cooling on turbine rotor blade

1. Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
2. China Gas Turbine Establishment, Aviation Industry Corporation of China, Chengdu 610500, China

摘要

摘要: 采用数值模拟的方法，研究了发动机工作条件下涡轮转子叶片压力面异型气膜孔的冷却特性，分析了吹风比和旋转雷诺数对气膜冷却的影响.结果表明：旋转条件下，气膜射流受离心力和哥氏力作用朝叶尖方向发生偏转，射流涡结构发生改变；随着旋转雷诺数增大，气膜射流向叶尖的偏转量逐渐增加，展向冷却均匀性提高，展向平均冷却效率略有提升；同一转速下扇形孔和收敛缝型孔能有效抑制气膜分离，展向平均冷却效率沿下游单调变化，随吹风比增加而升高，吹风比越小气膜射流向叶尖偏转越明显；旋转条件下，扇形孔与收敛缝型孔射流较圆孔射流仍有明显的冷却优势.
- 涡轮转子叶片 /
- 异型孔 /
- 气膜冷却 /
- 吹风比 /
- 旋转雷诺数
Abstract: Numerical simulations were conducted to investigate the shaped-hole film cooling on the pressure side of a turbine rotor under engine operating conditions, including the effects of blowing ratio and rotational Reynolds number. Results showed that the film jet was deflected towards the blade tip subjecting to the combined influences of centrifugal force and Coriolis force under rotational conditions, due to the change of the film vortex structure. The film jet was deflected towards the blade tip more sharply with the increase of rotational Reynolds number. The laterally-average cooling effectiveness slightly improved owing to more uniform film coverage. In the same rotational speed, the fan-shaped hole and console hole enabled to effectively restrain the film separation with high blowing ratios compared with the cylindrical hole. The laterally-average cooling effectiveness monotonously decreased downstream and increased with the blowing ratio. Besides, the film jet bent to the tip more notably with a small blowing ratio. As a result, the fan-shaped hole and console hole still have a pronounced advantage over the cylindrical hole under rotational conditions.
- turbine rotor blade /
- shaped-hole /
- film cooling /
- blowing ratio /
- rotational Reynolds number

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参考文献(22)

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