Abstract
The three-dimensional viscous compressible flow in the interblade channel of a turbomachine blade row is examined. A mathematical model of steadystate separated turbulent polytropic-gas flow with allowance for wall flow effects is proposed. It is assumed that the thickness of the boundary layers and the scales of the wall flow interaction zones are small as compared with the characteristic dimension of the system. Subsonic flow calculations are made for near-design flow regimes.
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