摘要
为了进一步理解双出口气膜孔的冷却特性,建立了气膜冷却效率实验台,通过红外测温技术研究了圆孔和4个不同次孔方位角的双出口孔在吹风比为0.3~2.0时的冷却效率.结果表明：和圆孔相比,次孔方位角为30°,45°,60°双出口孔能提高面平均冷却效率18%~37%.次孔方位角为30°双出口孔在低吹风比下提高冷却效率最显著,次孔方位角为60°双出口孔在高吹风比下提高冷却效率最显著.在研究的吹风比范围内,次孔方位角为45°双出口孔都能较显著地提高冷却效率,次孔方位角为75°双出口孔冷却效率低于圆孔冷却效率.
In order to understand the cooling characteristics of the double-outlet film holes further,the platform for testing film cooling effectiveness was established.The cooling effectiveness of the cycle holes and four kinds of double-outlet holes with various orientation angles was studied at the blowing ratios from 0.3to 2.0by infrared measurement.The results show that：compared with the cycle hole,the surface averaged cooling effectiveness of the double-outlet holes is improved by 18%-37% with 30,45and 60degrees of orientation angles.At the low blowing ratios,the cooling effectiveness of the double-outlet holes with 30degree of orientation angles is most significantly improved.At the high blowing ratios,the cooling effectiveness of double-outlet holes with 60degree of orientation angles is most significantly improved.The double-outlet holes with 45degree orientation angles can significantly improve the cooling effectiveness at both high and low blowing ratios.The cooling effectiveness of the double-outlet holes with 75degree of orientation angles is lower than that of the cylindrical holes.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2014年第5期1029-1035,共7页
Journal of Aerospace Power
基金
国家自然科学基金(51306126)
航空科学基金(2012ZB54006)
关键词
航空发动机
涡轮叶片
气膜冷却
冷却效率
双出口孔
aero-engine
turbomachine blades
film cooling
cooling effectiveness
double-outlet hole
