次孔方位角对单入口-双出口孔射流气膜冷却效率影响

李广超; 吴冬; 张魏; 柏树生

次孔方位角对单入口-双出口孔射流气膜冷却效率影响

沈阳航空航天大学动力与能源工程学院辽宁省数字化工艺仿真与试验技术重点实验室, 沈阳 110136

基金项目: 航空科学基金(2010ZB54004); 辽宁省教育厅基金(LZ2010425)

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出版历程
- 收稿日期: 2010-06-17
- 修回日期: 2010-12-20
- 刊出日期: 2011-07-28

Influence of orientation angles of branch hole on film cooling effectiveness with one inlet and double outlet hole injection

Liaoning Key Laboratory of Digital Technology Simulation and Test Technique, College of Power and Energy Engineering, Shenyang Aerospace University,Shenyang 110136,China

摘要

摘要: 为了探讨次孔方位角对单入口-双出口孔射流气膜冷却效率的影响,利用商业软件提供的有限体积法求解Navier-Stokes方程,对次孔方位角分别为30°,45°,60°和90°的单入口-双出口孔射流冷却效率进行数值模拟.吹风比变化范围为0.5~2.0.研究了流场、气膜冷却效率和径向平均气膜冷却效率的变化规律.结果表明,相对于圆柱孔,单入口-双出口孔射流气膜冷却效率明显改进.基于气膜冷却效率的最佳次孔方位角度为45°,高于圆柱孔射流气膜冷却效率300%.吹风比越大,次孔方位角对气膜冷却效率的影响越明显.
- 航空发动机 /
- 涡轮叶片 /
- 气膜冷却效率 /
- 次孔方位角 /
- 数值模拟
Abstract: In order to investigate the influence of orientation angles of branch hole on film cooling effectiveness with one inlet and double outlet hole injection, the film cooling effectiveness was simulated by commercial code using the finite volume method, on the condition that the orientation angles of branch hole were 30°, 45°, 60° and 90° respectively, the blowing ratios varied from 0.5 to 2.0 . The flow field, the film cooling effectiveness and the spanwise averaged film cooling effectiveness were investigated. The results show that the film cooling effectiveness with one inlet and double outlet hole injection has been improved as compared to that of the cylindrical hole injection. The optimized branch hole angle is 45°, higher by 300% than the film cooling effectiveness of the cylindrical hole injection. The orientation angles of branch hole have an increasing influence on the film cooling effectiveness with the increase of blowing ratios.
- aircraft engines /
- turbine blade /
- film cooling effectiveness /
- orientation angle of branch hole /
- numerical simulation

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参考文献(17)

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