摘要
当动叶转角增加以进一步提升亚声速轴流压气机级负荷时,为解决其内部流动问题,提出了基于轴向速度提升的亚声速低反动度轴流压气机气动设计原理.分析了在该气动设计原理指导下,各气动参数间的相互影响,设计了一个验证级.三维黏性数值模拟结果表明:在叶尖切线速度为213m/s的前提下,实现了级压比为1.5,效率为92.5%的压气机级设计.
An aerodynamic design principle for subsonic axial-flow compressor with low reaction based on enhanced axial velocity was proposed to solve the internal flow problems when the stage load was further enhanced by increasing the turning angle of the flow in the rotor. The mutual interactions between each aerodynamic parameter were analyzed based on this aerodynamic design principle, and a verification stage had been designed. The three-di- mensional viscous numerical simulation results show that a compressor design of stage pres- sure ratio of 1.5 with efficiency of 92.5% at tip tangential speed of 213 m/s has been attained.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2014年第3期708-718,共11页
Journal of Aerospace Power
关键词
低反动度
轴流压气机
亚声速
附面层抽吸
高负荷
low reaction
axial-flow compressor
subsonic
boundary layer suction
highly-loaded
