小孔辅助结构影响气膜冷却效果的实验

刘晓红; 陶智; 罗翔

小孔辅助结构影响气膜冷却效果的实验

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国家级重点实验室, 北京 100191

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出版历程
- 收稿日期: 2011-01-11
- 修回日期: 2011-03-04
- 刊出日期: 2011-12-28

Experimental investigation on effect of small auxiliary holes on film cooling effectiveness

National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 采用稳态液晶测温方法,详细研究了具有辅助小孔的分叉孔和大小孔的冷却效率分布规律,并与圆柱孔和扇形孔进行对比,分析小孔辅助结构对气膜冷却效果的影响.实验参数:主流雷诺数为2900,吹风比为0.3~3.0,密度比为1.06.结果表明:所有工况下,小孔辅助结构均在一定程度上提高气膜冷却效果,吹风比越大,对气膜冷却效果的改善就越明显,并且大小孔的冷却效率始终高于分叉孔.扇形孔只在吹风比大于1.0时,才起到改善气膜冷却效果的作用.
- 气膜冷却 /
- 冷却效率 /
- 液晶 /
- 辅助小孔 /
- 吹风比
Abstract: Experimental study was conducted to investigate the effect of small auxiliary holes on the film cooling performance.The steady-state thermochromic liquid crystal (TLC) method was used to obtain the adiabatic effectiveness distributions on the flat surface.Measurements of adiabatic effectiveness were presented for cylindrical hole,fan-shaped hole,furcated hole and parallel hole with main flow Reynolds number at 2900,blowing ratio ranging from 0.3 to 3.0 and density ratio at 1.06.Results show that the film coverage and adiabatic effectiveness downstream of furcated hole and parallel hole are evidently superior to those of cylindrical hole at blowing ratios range from 0.3 to 3.0.While fan-shaped hole increases the adiabatic effectiveness compared with cylindrical hole only in cases of blowing ratios greater than 1.0.A higher blowing ratio means more obvious improvement of the adiabatic effectiveness.
- film cooling /
- adiabatic effectiveness /
- liquid crystal /
- small auxiliary hole /
- blowing ratio

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参考文献(12)

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