Abstract
An intercooling technique using convective cooling channels in the compressor stator vanes has been proposed recently. In this paper, two cooling methods are presented, and numerical simulation is conducted using the conjugate heat transfer method to study the effect of cooling on the laminar boundary layer and turbulent boundary layer in compressors. A flat plate and a two-dimensional compressor vane are numerically simulated to study the effect of cooling on the two-dimensional boundary layer on the flat plate and curved surface, respectively. It is found that cooling decreases the size of the laminar separation bubble and delays turbulent separation; this reduces the drag coefficient at both design and off-design angle of attack. Further, a three-dimensional compressor vane with cooling channels and cooling endwalls is also numerically simulated. It is found that the cooling channels decrease the total pressure loss at the corner separation region; this proves that the proposed cooling method can be applied as a flow control method in the compressor.
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