Abstract
The NURBS (non-uniform rational B-spline) method was introduced for the 3D geometric optimization of axial flow compressor blade design. A set of optimization rule was developed by relating some aerodynamic performance parameters with the weights factor of NURBS. In the design of an axial compressor stator blade, the flow structures comparison have been made between the optimized new blade and the original one. The results show that this method could flexibly and rapidly optimize the blade shape to meet the aerodynamic requirements.
| Original language | English |
|---|---|
| Pages (from-to) | 625-629 |
| Number of pages | 5 |
| Journal | Hangkong Dongli Xuebao/Journal of Aerospace Power |
| Volume | 20 |
| Issue number | 4 |
| State | Published - Aug 2005 |
Keywords
- Aerospace propulsion system
- Axial flow compressor blade
- Blade design
- Non-uniform rational B-spline
- Shape optimization