Abstract
Blocked structure three-dimensional Navier-Stokes flow solver has been developed and applied to investigate the complex flow phenomena in the tip gap of axial flow compressor cascade. Numerical analysis was carried out to investigate the influence of tip clearance on the flow-field in a compressor cascade with a moving end-wall. The calculated results were compared with the available experimental data and good agreements were achieved. Secondary traverse flow velocity vector plots show the scrapping of the tip leakage vortex from the suction surface of one blade across the blade pitch to the pressure surface of the adjacent blade.
| Original language | English |
|---|---|
| Pages (from-to) | 112-118 |
| Number of pages | 7 |
| Journal | Hangkong Dongli Xuebao/Journal of Aerospace Power |
| Volume | 21 |
| Issue number | 1 |
| State | Published - Feb 2006 |
Keywords
- Aerospace propulsion system
- Compressor cascade
- Moving end-wall
- Scrapped tip leakage vortex
- Tip clearance flow