摘要
采用Realizable k-ε紊流模型,前缘滞止线两侧孔排采用负角度对吹式、其它孔排采用α=30°、β=45°复合角度射流孔,定义叶片表面为无滑移绝热壁面,主流温度Tm=473.15K,射流温度Tc=293.15K,对不同吹风比下叶片表面的气膜冷却效率及流线进行了分析。结果表明:随着吹风比的增加,叶片压力面侧的气膜冷却效率明显提高,叶片前缘处冷却效率略有提高,叶片吸力面侧可形成连续的气膜,气膜冷却效率较高;在滞止线两侧采用单一角度叉排对吹式孔排虽然可以提高该处气膜冷却效率,但此处射流对主流的扰动也比较强烈;复合角度射流的优势在局部主流速度较高的情况下能得到很好的体现。
The Realizable k-ε turbulence model was adopted to investigate the cooling efficiency and streamlines of gas film on turbine blade surface with different blowing ratios. The jet holes on both sides of the stagnation line in front edge adopted negative angle opposed blowing, and other holes used compound angle blowing with α of 30° and β of 45°. Define that the blade surface is no- slip adiabatic wall,the mainstream temperature Tm is 473. 15 K and the jet-flow temperature Tc is 293.15 K. The results revealed that,with an increase in blowing ratio,for pressure surface of the static blade, the cooling efficiency of gas film increased sharply while that at front edge of the blade increased slightly ; for suction surface of the blade, continuous film was formed,resulting in high cooling efficiency of the gas film. Using single angle cross-row configuration for jet holes at both sides of the stagnation line could enhance the film cooling efficiency, but with this method the jet disturbance to the main stream was strong. The advantage of compound angle jet could be well demonstrated when the local velocity of main stream was high.
出处
《热力发电》
CAS
北大核心
2014年第2期79-86,共8页
Thermal Power Generation
关键词
气膜冷却效率
复合角度
静叶栅
数值研究
film coolin efficiency
compound angle stator blade numerical simulation
