Investigation of Cooling Effect on the Aerodynamic Performance in the Intercooled Compressor

摘要

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