The experimental analysis of the flow that develops in a two stage axial flow compressor at off-design conditions is presented. The measurements are performed upstream, between and downstream of the four blade rows of the compressor. The analysis shows the off-design effects on the local conditions of the flow field. Low energy flow zones are identified, and the development of annulus boundary layer, secondary and tip clearance flows, are shown. The tip clearance flows are also present in the stator rows with various outlying conditions (stationary or rotating hub).

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