Abstract
A flowfield simulation code was developed based on Reynolds-averaged Navier-Stokes equations and validated by experimental data. A numerical optimization code was developed and applied to the optimization design of a circumferentially curved transonic compressor rotor. Results indicate that the circumferential curving can effectively change the three dimensional shock wave structures and weaken wake losses. Optimized blades improve adiabatic efficiency approximately 0.59% and possess fine off-design performance.
| Original language | English |
|---|---|
| Pages (from-to) | 480-484 |
| Number of pages | 5 |
| Journal | Hangkong Dongli Xuebao/Journal of Aerospace Power |
| Volume | 21 |
| Issue number | 3 |
| Publication status | Published - Jun 2006 |
| Externally published | Yes |
Keywords
- Aerospace propulsion system
- Circumferential curving
- Compressor rotor
- N-S equations
- Optimization design