Abstract
For an improvement of aerodynamic performances of axial-flow compressors, effects of tip clearances on the suction-corner flow of the blade cascades were studied by cascade-wind-tunnel tests. The cascade pressure-recovery coefficients were found to improve by about 5 % for an optimum small tip clearance (0.4mm for the chord length of 100 mm). The measured distributions of total pressure and the visualized flow patters on the end-wall evidenced the structure of the improved end-wall flow. The phenomenon is promising for the future improvement of the machine, although the tip clearance is too small for practical application at the present level of technology.
