Abstract
The effect of by-pass flow ratio on fan/compressor performance was studied. Modification of boundary layer thickness on end wall and effect of splitter lip were discussed. The two-stage fan and six-stage high pressure compressor of YTF-33 turbofan engine were considered as numerical examples. The performance curves for the fan stream, engine stream and six-stage compressor were given, which were in agreement with test data provided by wall R.A.. It is shown that the by-pass flow ratio has considerable effect on the high pressure compressor performance, but a small effect on fan performance. In order to optimize fan/compressor performance the splitter lip shape should be carefully matched with the axial location.
| Original language | English |
|---|---|
| Pages (from-to) | 349-352 |
| Number of pages | 4 |
| Journal | Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University |
| Volume | 19 |
| Issue number | 3 |
| State | Published - Aug 2001 |
Keywords
- By-pass ratio
- Fan/compressor performance
- Splitter lip