Effect of in-service burnout effect on the transonic leakage flows over cavity tip model

Increasing the gas temperature at inlet to high pressure turbine of engines is known as a proven method increase efficiency these engines. However, this will expose blades’ surface very heat load and thermal damages. In case un-shrouded blades, blade tip be exposed significant due developed leakage flows in gap, leads in-service burnout which degrades shortens its operational life. This paper studies effect transonic over cavity configuration commonly used reduce flows. investigation carried out experimentally within wind tunnel computationally using steady unsteady Reynolds Averaged Navier Stokes approaches. Various flow measurements are established different behaviour including separation bubbles, shockwave development distinct interactions captured discussed. It found that when burnout, behaves significantly way. addition, effective gap becomes much larger allows higher mass rate comparison sharp-edge (i.e. beginning life). The losses for round-edge burn-out effect). Experimental computational visualisations, discharge coefficient variation given analysed several ratios across gap.