Abstract
A numerical study on the effect of different tip clearance size on the performance of a low aspect ratio transonic fan with tandem cascade has been carried through. Five different levels of relatively tip clearances are 0%, 0.132%, 0.396%, 0.66%, 1.32% respectively. The result indicates that with the increase of tip clearance size, the performance of fan stage changes obviously. Tip clearance influences shock and interaction between shock and boundary layer near the tip for transonic fan/compressor. The block and loss at tip region has great important relation with the leakage flow.
| Original language | English |
|---|---|
| Pages (from-to) | 1653-1656 |
| Number of pages | 4 |
| Journal | Kung Cheng Je Wu Li Hsueh Pao/Journal of Engineering Thermophysics |
| Volume | 29 |
| Issue number | 10 |
| State | Published - Oct 2008 |
| Externally published | Yes |
Keywords
- Numerical simulation
- Tip clearance
- Transonic fan
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