摘要
为研究某压气机内部流场结构,采用全流道非定常数值模拟方法,对跨声速压气机最高效率点和近失速点流场进行求解,重点分析近失速工况下压气机内部流场结构.研究表明:在近失速工况下,动叶槽道激波前推与前缘脱体激波融合为一道激波,强度增强;动叶20%叶高处激波前推最为严重,引起动叶吸力面附面层严重分离;静叶根部受上游动叶尾迹影响形成大范围的分离区,并有空间环涡结构形成.
Full-annulus unsteady simulations were carried out to obtain the internal flow field structure in an axial flow com- pressor at design point and near stall point, especially the in- ternal flow of compressor at stall point was studied. Results show that, at near stall point, shock waves in rotor passages move forward, and form stronger shock waves by combining with the detached shock waves. The shock waves at 20% span of rotor move forward most seriously, leading to a heavy boundary separation on the rotor suction side. Influenced by rotor wake flow, large scale separation zones generated at sta- tor corner and space ring vortex formed.
出处
《大连海事大学学报》
CAS
CSCD
北大核心
2015年第2期77-83,共7页
Journal of Dalian Maritime University
基金
国家自然科学基金资助项目(51006014)
中央高校基本科研业务费专项资金资助(3132014048)
关键词
压气机
流场结构
非定常
激波
分离
compressor
flow-field
unsteady
shock wave
separation
