Abstract
A set of process for calculating primitive cascades minimum throat area ratio was built, in order to study the effects of minimum throat area ratio on multistage axial-flow compressor performance. The span-wise distribution of minimum throat area ratio was obtained through calculating primitive cascade, and the minimum throat ratio distribution rule of rotor and stator are analyzed. Then the front camber ratio and maximum thickness of primitive blade was modified to study the different distribution of minimum throat area ratio impacting on multistage axial-flow compressor performance. The result shows that block mass-flow and minimum throat area ratio have a linear relationship. Having a best front camber ratio makes the compressor total pressure ratio and efficiency to achieve the maximum at design point. And reducing thickness is able to improve compressor performance.
| Original language | English |
|---|---|
| Pages (from-to) | 47-53 |
| Number of pages | 7 |
| Journal | Tuijin Jishu/Journal of Propulsion Technology |
| Volume | 36 |
| Issue number | 1 |
| DOIs | |
| State | Published - 1 Jan 2015 |
Keywords
- Block mass-flow
- Camber ratio
- Maximum thickness
- Multistage compressor
- Primitive blade
- Throat area ratio