高负荷正预旋子午较大后掠转子的一种尖部气动失稳
Tip Aerodynamic Instability of High Load Rotor with Preswirl and Excess Meridional Backswept
-
摘要: 在高通流高负荷风扇预研中, 遇到了设计常规轴流压气机时并不显现的新现象: 在级增压比为 2.33, 转子叶尖半径 0.4414m,切线速度 490 m/s的单级实验后掠风扇 ATS-2有预旋方案的通流设计中, 转子叶尖流动滞止并且不收敛, 或非正常地收敛。Abstract: An unusual aerodynamic phenomenon is encountered in designing a high through flow,high load single stage backswept fan.The fan is one of the two base schemes of the model fan ATS 2 with preswirl incoming flow and stage pressure ratio 2.33,tip radius 0.4414 m,tip velocity 490 m/s.In the flow calculation of S2m stream surface streamline curvature,the flow near the rotor tip stagnates unavoidably and the iteration does not converge or converges irregularly.It is found out from the analysis that the phenomenon is mainly associated with the excess backswept of the rotor leading edge.
-
Key words:
- compressors /
- rotors /
- gasdynamics
点击查看大图
计量
- 文章访问数: 1424
- HTML浏览量: 4
- PDF量: 400
- 被引次数: 0