Experimental and Numerical Study on the Combined Jet Impingement and Film Cooling of an Aero-Engine Afterburner Section

The recent advancement of cooling methodologies for critical components such as turbine blades, combustor liners, and afterburner liners has led to the development a combination impingement film cooling. present study proposes an efficient technique modern aero-engine liner based on jet To achieve this, numerical model is devised flow over corrugated with several jets impinging it. validated in set in-house experiments well against experimental data available literature. experiment performed limited temperature range (i.e., low-density ratio). However, simulations are carried out by varying blowing ratio from 0.3 0.6. density during kept at 3.5. minimum distance between plate h/D = 1. A detailed analysis results indicates significant drop distribution surface because employed technique. also reveals that, under similar operating conditions, combined system ability targeted effect lower bleed air rate due its higher effectiveness than that standard arrangement.