Abstract
A numerical procedure is presented for predicting flow-field around splitter lip in a fan/compressor system. An improved singularity method is used to obtain the potential flow field along splitter surface and subsequently a turbulent boundary layer analysis is applied. A number of different splitter lip geometries are analyzed and their effects on flow field near the splitter lip are discussed under two incidence angles. Some conclusions are drawn based on the numerical results, which are helpful to improve the splitter lip design performance.
| Original language | English |
|---|---|
| Pages (from-to) | 215-217 |
| Number of pages | 3 |
| Journal | Jixie Kexue Yu Jishu/Mechanical Science and Technology |
| Volume | 20 |
| Issue number | 2 |
| State | Published - Mar 2001 |
Keywords
- Fan/Compressor
- Splitter lip
- Turbulent layer