Abstract
Based on steady numerical simulation of contra-rotating compressor in lab, a numerical investigation of the rotating stall mechanism of a contra-rotating axial flow compressor was conducted. The study shows that: (1) the rotating stall inception which appears near the stall point is "spike" type; (2) the tip clearance vortex in rotor 2 develops rapidly near the stall point and the passage is chocked, which cause the instability of the whole compressor; (3) the aerodynamic stability of compressor is determined by the development of tip clearance vortex in rotor 2 because of the high loading on the blades.
| Original language | English |
|---|---|
| Pages (from-to) | 188-194 |
| Number of pages | 7 |
| Journal | Hangkong Dongli Xuebao/Journal of Aerospace Power |
| Volume | 28 |
| Issue number | 1 |
| State | Published - Jan 2013 |
Keywords
- Contra-rotating compressor
- Near stall condition
- Numerical investigation
- Rotating stall mechanism
- Tip clearance leakage