Study of Shock Wave Control by Suction & Blowing on a Highly-loaded Transonic Compressor Cascade

A numerical investigation of shock wave control over a highly-loaded transonic compressor blade is presented in the current work. Two types of active flow control methods, namely blowing and suction, are employed. Their effectiveness in controlling the shock wave boundary layer interaction in the intended cascade passage has been investigated numerically. The three-dimensional RANS equations in Cartesian coordinate system are solved using the cell-centred control volume approach. Blowing and suction at four locations along the blade are simulated. Aerodynamic performance is evaluated for each case in terms of total pressure recovery coefficient, deviation angle, etc. Results show that blowing is not capable of providing desired control outcome, as the effects can only be seen in the neighbourhood of the blowing slot. The reconfiguration of shock waves in cascade is realized by suction through the slots located downstream after shock waves. Both the right branch of leading edge shock and the passage shock wave move downstream toward the suction slot. Compared with the baseline case, the suction with a suction ratio of 1.2% from slot D (at the 51% Chord) increased the total pressure recovery coefficient by 10%, and decreased the deviation angle by 5 degrees.