摘要
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.
| 源语言 | 英语 |
|---|---|
| 页（从-至） | 349-352 |
| 页数 | 4 |
| 期刊 | Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University |
| 卷 | 19 |
| 期 | 3 |
| 出版状态 | 已出版 - 8月 2001 |