发动机进口整流支板端部流场  

The flow field of entrance strut in aero-engine

作　　者：马驰[1] 王涵[1] 桂琳[1] 马树元[1] 王建明[1] 

机构地区：[1]沈阳航空航天大学辽宁省航空推进系统先进测试技术重点实验室,沈阳110136

出　　处：《沈阳航空航天大学学报》2016年第3期25-31,共7页Journal of Shenyang Aerospace University

基　　金：航空科学基金(项目编号:2011ZA54002)

摘　　要：数值模拟了发动机进口整流支板端部流动情况,分析了整流支板下游流场的分布规律,对比分析了发动机进口整流支板调节角度为0°和30°时的流场差别。研究结果表明,整流支板端壁区的马蹄涡可延伸至支板下游较远距离,至少可达两倍支板弦长;马蹄涡在支板下游流场发展过程中涡心涡量逐渐减弱,涡空间范围逐渐增大;整流支板调节角度为30°时支板周围及下游的总压损失系数是调节角度为0°时的3倍。Numerical simulation was carried out to investigate the flow structure around the entrance strut in aero-engine,especially the downstream flow field of strut. Flow fields around aero-engine struts with different regulated angles( 0°and 30°) were compared and analyzed. The results show that horseshoe vortex near the surface of the strut can extend to the downstream flow field of the strut,which is twice as long as length chord of the strut. The vorticity of vortex core decreases gradually but the space scale of horseshoe vortex increases progressively as the horseshoe vortex goes to the downstream flow field of strut. The total pressure loss coefficient of down stream field for strut with regulated angle of 30° is three times as that for strut with regulated angle of 0°。

关 键 词：压气机 进口整流支板 马蹄涡 流动结构 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]