Abstract
In this paper, we investigate the aerodynamic performance and flow field of dual-stage counter-rotating compressor using the numerical simulation based on the parallel computation technique. The aim is to study the influence of the stagger angle of the inlet guide vane, which include the aerodynamic performance of the whole compressor and the inlet flow angle of each blade row. The result demonstrates: (1) computation efficiency is improved using the parallel computation technique based on three personal computers; (2) the stagger angle of IGV have an influence on the aerodynamic performance of counter-rotating compressor; (3) The inlet flow angle increases for Rotor 1 and decreases for OGV with adjusting IGV to the anti-clocking-wise, so the total pressure ratio is improved, efficiency is nearly constant and the work range is extended a little.
| Original language | English |
|---|---|
| Pages (from-to) | 573-576 |
| Number of pages | 4 |
| Journal | Kung Cheng Je Wu Li Hsueh Pao/Journal of Engineering Thermophysics |
| Volume | 31 |
| Issue number | 4 |
| State | Published - Apr 2010 |
Keywords
- Aerodynamic performance
- Counter-rotating compressor
- Inlet guide vane adjustment