弯曲多孔壁不同倾斜角气膜孔整体气膜冷却效率研究

赵梦梦; 张弛; 林宇震; 刘高恩

弯曲多孔壁不同倾斜角气膜孔整体气膜冷却效率研究

北京航空航天大学能源与动力工程学院航空发动机气动热力重点实验室, 北京 100083

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出版历程
- 收稿日期: 2006-01-20
- 修回日期: 2006-05-08
- 刊出日期: 2007-02-28

Study of overall cooling effectiveness of discrete holes with different angles to concave wall

National Key Laboratory on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

摘要

摘要: 对弯曲多孔壁气膜冷却整体冷却效率进行了深入研究.弯曲多孔壁由等曲率凹壁面多孔壁实验板来模拟, 实验研究了相同排列方式下2种不同小孔倾角方案整体气膜冷却效率, 分析了弯曲通道曲率对冷却效率的影响, 得到了沿流程的展向平均冷却效率及x/d=21.8和x/d=65.3处展向冷却效率分布.研究结果表明, 吹风比是影响凹壁面小孔气膜冷却效率的关键因素;随着吹风比的增大, 2种孔倾角冷却效率的差异变小;主流通道中气体的流动规律对冷却效率有较大影响.
- 航空、航天推进系统 /
- 航空发动机 /
- 回流燃烧室 /
- 弯曲通道 /
- 冷却效率
Abstract: Overall cooling effectiveness of curved walls with discrete angled holes has been studied in the paper through approximate simulation employing experimental concave walls with a constant curvature,which were applied intensively in the curved duct for turboshaft engine reverse-flow combustor.An experiment by heat transfer method for the overall cooling effectiveness was performed and the effect of blowing ratio on the overall spanwise averaged cooling effectiveness was obtained.The experimental result shows an improved overall cooling performance for the curved wall and the insignificant difference between the discrete holes with 30° inclined angle and normal to the concave wall at high blowing ratio.The flow in the curved duct has influence on the overall cooling effectiveness significantly.
- aerospace propulsion system /
- aircraft engine /
- reverse-flow combustion chambers /
- curved tube flow /
- cooling effectiveness

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参考文献(12)

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