吸力面射流对涡轮激波/附面层干涉的影响  

Effect of Suction Side Jet on Shock Wave/Boundary- layer Interactions in Turbine Cascade

作　　者：刘建[1] 乔渭阳[1] 魏佐君[1] 段文华[1] LIU Jian;QIAO Wei-yang;WEI Zuo-jun;DUAN Wen-hua(School of Power and Energy,Northwestern Polytechnical University,Xi'an 710072,China)

机构地区：[1]西北工业大学动力与能源学院

出　　处：《航空计算技术》2019年第3期78-82,共5页Aeronautical Computing Technique

摘　　要：随着涡轮级负荷增大,跨声速涡轮中激波损失在总损失中所占比例越来越大。采用大涡模拟方法对跨声速涡轮叶栅吸力面喉部位置射流对激波/附面层干涉(SWBLI)的影响进行研究。结果表明:射流的引入会加强入射激波强度和SWBLI,但分离泡长度有所减小。激波加强了叶片表面压力波动,在各激波位置波动达到幅值,最大波动幅值达当地时均压力的13%;加入射流后,射流下游吸力面压力波动水平增加,但是SWBLI造成的流动非定常性明显减弱。The loss induced by shock wave in the transonic/supersonic turbines is becoming increasingly prominent with increase of stage loading.The influence of round jet upstream the throat on the suction surface on shock wave boundary-layer interactions (SWBLI) in a transonic turbine cascade is investigated with large eddy simulation (LES).The results indicate that jet will strengthen the interactions on the suction surface,but the separation bubble is still decreased.The pressure fluctuation is strengthened in the SWBLI region,the peak value of pressure fluctuation is about 13% of the local averaged pressure for the no jet case;but for the jet case,the peak value exists in the jet region,the flow unsteadiness induced by SWBLI is weakened.

关 键 词：大涡模拟 射流 激波/附面层干涉 波系结构 分离泡 压力波动 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]