摘要
Based on the experiment in different condition, three-dimensional flow field of an axial-centrifugal combined compressor has been investigated by numerical simulation. In order to improve the performance of the axial-centrifugal combined compressor; the setting angel of inlet guide vane and first stator vane is changed. The investigation of numerical simulation and performance calculation for the axial-centrifugal compressor indicates that optimization of stator vane angle can enlarge stall and surge margin, weaken shock and improve the flow field structure in some blade rows. And the peak efficiency is increased by 1.05%, without changing the total pressure ratio at 90% design speed after changing angles of the inlet guide vanes and first stator vanes.
| 源语言 | 英语 |
|---|---|
| 页（从-至） | 356-361 |
| 页数 | 6 |
| 期刊 | Tuijin Jishu/Journal of Propulsion Technology |
| 卷 | 28 |
| 期 | 4 |
| 出版状态 | 已出版 - 8月 2007 |