Abstract
The aerodynamic numerical optimization method based on the adaptive genetic algorithm in house software is investigated. Adopting this method which is composed of design of experiment, neural network response model and numerical simulation software, the global optimization can be implemented automatically. The compressor cascade endwall has been optimized by the parameterization of endwall surface and the influence of the non-axisymmetric endwall on its aerodynamic performance is analyzed. The results show that the contouring endwall can effectively change the near endwall static pressure to improve the corner flow and decrease the loss of the secondary flow. Comparing with the datum cascade, the total pressure loss is reduced by 27.8% and the static pressure ratio is increased by 19% in the non-axisymmetric endwall.
| Original language | English |
|---|---|
| Pages (from-to) | 1047-1050 |
| Number of pages | 4 |
| Journal | Kung Cheng Je Wu Li Hsueh Pao/Journal of Engineering Thermophysics |
| Volume | 34 |
| Issue number | 6 |
| State | Published - Jun 2013 |
Keywords
- Compressor cascade
- Design optimization
- Non-axisymmetric endwall
- Secondary flow
Fingerprint
Dive into the research topics of 'Design optimization of non-axisymmetric endwall contouring in compressor cascade'. Together they form a unique fingerprint.Cite this
- APA
- Author
- BIBTEX
- Harvard
- Standard
- RIS
- Vancouver