摘要
通过数值模拟,研究了涡轮叶片弦中区所采用的新型双层腔冷却结构的冷却特性,系统分析了冲击气膜组合冷却的流动与换热特性,讨论了冷气进口雷诺数Re、吹风比M以及气膜孔与冲击孔的直径比D/d对组合冷却效果的影响。计算参数范围是：冷气进口雷诺数Re=2 000～5 000,吹风比M=0.6～2.0。计算结果表明,冷气进口Re,M以及D/d对双层腔结构冷却效果的影响非常明显,在计算范围内：（1）Re和M越高,冷却效果越好;（2）当冲击孔直径一定时,增加气膜孔的直径,冷却效果会随之增加;（3）当冲击孔直径一定时,增加气膜孔的直径,流阻系数会随之减小。
The present study concentrates on the computational investigation of a new cooling configuration of a double-layer cavity in the middle section of modern turbine blade.A three-dimensional Navier-Stokes code with standard k-ε turbulence model as well as wall functions is used to compute the flow and heat transfer characteristics for a combined impingement and film cooling configuration.The blowing ratio ranges of 0.6～2.0,and the Reynolds number based on the inlet velocity of the cooling air varies from 2 000 to 5 000.Details of the effect of the ratio of film hole diameter to jet hole diameter,D/d on hybrid cooling effectiveness are discussed.Numerical results show that a larger hybrid cooling effectiveness and a lower flow resistance are reached with the increase of the diameter of film cooling hole,while the diameter of impingement hole is fixed.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2008年第4期823-828,共6页
Acta Aeronautica et Astronautica Sinica
基金
教育部"新世纪优秀人才支持计划"(NCET-05-0189)
"凡舟"青年科研基金(20070401)
关键词
气膜
冲击
组合
冷却
换热
流阻
film
impingement
hybrid
cooling
heat transfer
flow resistance
