摘要
采用Realizablek-ε紊流模型,并结合Simplec算法和有限元法对体积进行离散,研究了静止叶栅前缘射流孔在2种复合角度α=30°、β=45°和α=135°、β=45°,不同吹风比M=0.5、M=1.0、M=1.5,主流温度为T∞=293 K时的压力面和吸力面温度场,并分析了典型工况下的气膜冷却效率.结果表明:相同复合角度、不同吹风比的压力面和吸力面冷却效率曲线变化趋势一致;前缘复合角度射流对整个吸力面的冷却效率有较大影响,随着吹风比的增大,冷却效率提高;当前缘复合角度为α=30°、β=45°时,压力面冷却效率随着吹风比的增大而提高,而当前缘复合角度为α=135°、β=45°时,随着吹风比的增大,压力面的冷却效率降低.
Based on Simplec algorithm and combined with the finite element method to discretize the control equation,the realizable k-ε turbulence model was applied to simulate the temperature fields on pressure and suction surface of a stationary blade at different blowing ratio of M=0.5、M=1.0 and M=1.5 and the mainstream temperature is 293K,while the jet hole at the leading edge has compound angles of α=30°,β=45° and α=135°,β=45°.The film cooling efficiency was also analyzed for typical working conditions.Results show that with the same compound angle and different blowing ratio,the changing trend of the cooling efficiency curve of the pressure and suction surface is consistent,the compound angle jet at the leading edge has greater effect on the cooling efficiency of the suction surface.The cooling efficiency rises with increasing the blowing ratio.When the compound angle at the leading edge is α=30°、β=45°,the cooling efficiency of the pressure surface rises as the blowing ratio is increased.However,the cooling efficiency of the pressure surface reduces as the blowing ratio is increased when the compound angle at the leading edge is α=135°、β=45°.
出处
《动力工程》
CAS
CSCD
北大核心
2009年第10期919-925,共7页
Power Engineering
基金
国家自然科学基金资助项目(50606005)
关键词
燃气轮机
气膜冷却
复合角度
叶栅
温度场
冷却效率
数值模拟
gas turbine
air film cooling
compound angle
blade cascade
temperature field
cooling efficiency
numerical simulation
