AERODYNAMIC PERFORMANCE OF A HIGH-TURNING TURBINE CASCADE WITH VARYING TIP CLEARANCE*

Modern trends in gas turbine design have been geared to produce a compact high-workoutput engine as a power unit. To achieve this goal, preferring the turbine of high-turningangle blades, the experiments focused on the effects such as lift and pressure coefficients, that to be considered when the tip clearance and incidence angle are discussed for a linear cascade. The present study aims to investigate the effect of the tip clearance on loss mechanism in turbine blades using both experimental measurements as well as CFD numerical calculations. The flow measurements are obtained using a set of calibrated fivehole probe and multi-tube manometer to measure static pressure distribution on blade surfaces, total pressure loss coefficient, velocity distribution, etc. Important points are discussed and fruitful conclusions are drawn.