Abstract
The 3-D flow fields of a low-speed axial compressor rotor with a tip clearance were calculated. Compared with experimental results, effects of the tip grid-matching and the grid quality on numerical results were investigated. The result shows the requirement of the gird-matching between the tip clearance and the rotor passage for simulations of flow details in the tip clearance, and the sensitivity of the second-order difference scheme to the grid quality. In addition, it was revealed that the pressure rise characteristics did not exactly reflect the effect of grid numbers on numerical results.
| Original language | English |
|---|---|
| Pages (from-to) | 137-143 |
| Number of pages | 7 |
| Journal | Hangkong Dongli Xuebao/Journal of Aerospace Power |
| Volume | 21 |
| Issue number | 1 |
| State | Published - Feb 2006 |
Keywords
- 3-D flow field
- Aerospace propulsion system
- Compressor
- Gird
- Rotor
- Tip clearance
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