Abstract
A flow field solver code was developed based on three dimensional Navier-Stokes equations and validated by comparing the computational results with experimental data. A new global optimization strategy was described for computationally expensive aerodynamic design optimization problems, combined with improved-hypercube-sampling algorithm, a second-order polynomial response surface models (RSM), improved genetic algorithm (GA) and 3-D Navier-Stokes solver. This optimization method was applied to aerodynamic redesign of transonic compressor rotor with sweep and curve. The optimized rotor can evidently enhance the adiabatic efficiency and has fine off-design performance. The results showed that both the solver code and the optimization method have fine capability.
| Original language | English |
|---|---|
| Pages (from-to) | 510-514 |
| Number of pages | 5 |
| Journal | Tuijin Jishu/Journal of Propulsion Technology |
| Volume | 27 |
| Issue number | 6 |
| Publication status | Published - Dec 2006 |
| Externally published | Yes |
Keywords
- Compressor
- Design of experiments
- Genetic algorithms
- Numerical simulation
- Optimization design