抄録
For the next generation gas turbine, an advanced compressor which has higher pressure ratio and higher efficiency than the current is required. In the front stage, to achieve higher aerodynamic efficiency, transonic front stage airfoil design is focused on. In transonic blade, shock wave is the main source of loss, which is induced by the interference between shock wave and boundary layer and tip leakage flow. To reduce the loss, three-dimensional design concept which would manage the shock structure is examined for front stage transonic blade. The concept is studied by 3D CFD analysis. Results indicate S-shaped leading edge blade, which is characterized that forward swept in tip region, backward swept in hub to mean section, is effective to reduce shock loss at tip section, also maintains flow matching of original design intents.The actual shock wave in the 3D blade was visualized by PIV (Particle Image Velocimetry) measurement technology to check the shock structure. In this paper, the current results of 3D CFD study and shock visualization is presented.
