Abstract
Detailed measurements have been performed in a low pressure axial flow compressor stage to investigate the structure of the secondary flow field and the three-dimensional wake decay at different axial locations before and behind the rotor. The three dimensional flow field upstream and downstream of the rotor and on the centerline of the stator blade passage have been sampled periodically using a straight and a 90 degree triple-split fiber probe. Radial measurements at 39 radial stations were carried out at chosen axial positions in order to get the span-wise characteristics of the unsteady flow. Taking the experimental values of the unsteady flow velocities and turbulence properties, the effects of the rotor blade wake decay and secondary flow on the blade row spacing and stator passage flow at different operating conditions are discussed.
| Original language | English |
|---|---|
| Pages (from-to) | 11 |
| Number of pages | 11 |
| Journal | ASME Pap |
| Publication status | Published - 1996 |
| Event | Proceedings of the 1996 International Gas Turbine and Aeroengine Congress & Exhibition - Burmingham, UK Duration: 10 Jun 1996 → 13 Jun 1996 |
ASJC Scopus subject areas
- Mechanical Engineering
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