摘要
本文通过数值模拟的方法研究了主流马赫数对圆柱孔、扇形孔及双射流气膜孔三种不同气膜孔结构冷却效果及气动损失的影响规律。结果表明,主流马赫数增加对圆柱孔和扇形孔的冷却效果影响不大;在较高吹风比条件下双射流气膜孔的冷却效果受主流马赫数的影响较大:在距离气膜孔较近位置气膜冷却效果随马赫数增大显著提高,更远位置气膜冷却效果显著下降。不同气膜孔结构的气动损失在吹风比较小时十分接近,随着吹风比的增大气动损失随之增大,相同吹风比条件下,气动损失随主流马赫数的增加而减小。
Influence of different film cooling configurations on cooling effectiveness and aerodynamic losses of cylindrical hole, fanshaped hole and double-jet hole has been studied by numerical simulation method. The results indicate that mainstream mach number has little impact on film cooling effectiveness of cylindrical hole and fan-shaped hole. Mach numher has a great effect on film cooling effectiveness of double-jet hole with a high blowing ratio： the film cooling effectiveness in the area near the fihn cooling hole improves significantly with the increase of mainstream roach number. On the contrary, the film cooling effectiveness in the area further downstream the film cooling hole drops with the increase of mainstream roach number. The aerodynamic losses of different film cooling configurations are approximate when blowing ratio is low, and losses would increase with the blowing ratio rising. When the blowing ratio remains the same, the aerodynamic losses would drop with the increase of mainstream mach number.
出处
《燃气轮机技术》
2015年第2期15-20,72,共7页
Gas Turbine Technology
基金
国家自然科学基金项目(No.51336007)
关键词
主流马赫数
气膜冷却
气动损失
数值模拟
mainstream mach number
film cooling
aerodynamic losses
numerical simulation
