抄録
Experimental and numerical studies have been performed to investigate the inhibitory effects of partially shrouded blade tip on the tip leakage flow in a compressor linear cascade. The cascade is composed of seven blades with constant cross section from hub to tip. The airfoil cross section is representative of a typical rotor blade used in the rear stages of high loaded axial compressors. A moving belt, driven by a motor and a pulley system, runs linearly at constant speed under the horizontally suspended cascade to simulate the relative motion of the blade and the casing. Plates of three different sizes are installed respectively between the tip of the cascade and the moving belt, in order to imitate 20%, 40% and 60% shrouded blade tips. Traverse measurements in the pitch-wise and span-wise directions are made using a five-hole Pitot tube at the inlet and exit planes of the cascade. Reynolds-Averaged Navier-Stokes simulations have been conducted with the SST turbulence model and compared to experimental measurements. The experimental and numerical results showed the case of 60% shrouded blade tip could effectively reduce both the loss of the tip region and the overall loss.
