摘要
基于计算流体力学理论建立了气膜冷却射流的控制微分方程。采用Fluent对不同组合方式下双排孔射流气膜冷却特性进行了计算研究。根据实际工况,分析了不同吹风比下,上游孔顺向射流+下游孔顺向射流、上游孔顺向射流+下游孔逆向射流、上游孔逆向射流+下游孔顺向射流、上游孔逆向射流+下游孔逆向射流共4种不同组合结构的气膜冷却特性。结果表明,吹风比为0.3时,上游孔顺向射流+下游孔顺向射流组合展向平均气膜冷却效率较高,达到0.15左右;吹风比为0.8时,上游孔逆向射流+下游孔顺向射流组合展向平均气膜冷却效率较高,达到0.18左右;吹风比为1.4时,上游孔逆向射流+下游孔顺向射流组合展向平均气膜冷却效率,可以达到0.24左右。研究结果对涡轮叶片气孔结构设计有重要参考价值。
Based on the theory of computational fluid dynamics, the governing differential equation of film cooling jet was established. The film cooling characteristics of double row holes under different combination modes were calculated and studied by Fluent. According to the actual working conditions,the film cooling characteristics of four different combined structures under different blowing ratios were analyzed: upstream forward jet + downstream forward jet, upstream forward jet + downstream reverse jet,upstream reverse jet + downstream forward jet, upstream reverse jet + downstream reverse jet. The results show that when the blowing ratio is 0.3, the spanwise average film cooling efficiency of the combination of upstream forward jet and downstream forward jet is higher, which can reach about 0.15;When the blowing ratio is 0.8, the spanwise average film cooling efficiency of the combination of upstream reverse jet and downstream forward jet is higher, which can reach about 0.18;When the blowing ratio reaches 1.4,the spanwise average film cooling efficiency of the combination of upstream reverse jet and downstream forward jet can reach about 0.24. The conclusion has important reference value for the design of turbine blade pore structure.
作者
钟雅婷
汪才
杨欢
蔡鑫
ZHONG Ya-ting;WANG Cai;YANG Huan;CAI Xin(AVIC Chengdu aircraft(Group)Co.,Ltd.,Chengdu 610073,China;Shenyang Aerospace University,Shenyang 110136,China)
出处
《燃气涡轮试验与研究》
2022年第3期49-55,共7页
Gas Turbine Experiment and Research
关键词
气膜冷却
圆柱形气膜孔
逆向射流
射流叠加
涡轮叶片
气孔结构
film cooling
cylindrical film hole
reverse jet
jet superposition
turbine blades
stomatal structure
