Heat transfer characteristics of a high-pressure turbine under combined distorted hot-streak and residual swirl: an unsteady computational study

In new generation aero-engines, lean-burn combustors are equipped with swirl injectors in order to reduce pollutant emissions. At the exit of these combustors, flow is dominated by temperature non-uniformity (hot-streak) and residual swirl. Available research has focused mainly on isolated effects only or hot-streak aerodynamic performance thermal high-pressure turbine (HPT). Only few studies investigated combined aerothermal HPT using either idealized uniform rounded topologies. Realistic hot-streaks generated from lean burn have more complex topologies that involves distortions. The present study investigates distorted simultaneously a first stage HPT. Other types, rounded, been also without perform comparisons hot-streak. Unsteady Reynolds-averaged Navier–Stokes (URANS) computations conducted assess under influence different hot-streaks. Results revealed all were almost preserved as transported through vane altered rotor due secondary flows. Under swirl, remarkably at deformed exit. was homogenised dispersed. showed most transport behaviour stage. leakage tip gap high heat transfer rates, particular blade suction side surface. formed known vortex exit, which induced rates. found intensify consequently higher rates compared condition.