The breakdown of tip leakage vortex was examined on a low-speed axial compressor rotor with moderate blade loading. Effects of the breakdown on the rotor aerodynamics were elucidated by Navier-Stokes flow simulations and visualization techniques. The leakage vortex breakdown were observed inside the rotor at a lower flow rate than the peak pressure rise operating condition. The breakdown was characterized by the existence of the stagnation point followed by a bubble-like recirculating region. The onset of breakdown resulted to large expansion of the vortex and disappearance of the streamwise vorticity concentrated in the vortex.
|American Society of Mechanical Engineers (Paper)
|Published - 1998
|Proceedings of the 1998 International Gas Turbine & Aeroengine Congress & Exhibition - Stockholm, Sweden
Duration: Jun 2 1998 → Jun 5 1998
All Science Journal Classification (ASJC) codes
- Mechanical Engineering