Numerical simulation was carried out to study the effusion cooling on a specific transverse corrugated heat-shield used in aero-engine afterburner. Three main geometric parameters

including spanwise-to-streamwise pitch ratio

hole diameter and perforated percentage

were taken into consideration. Result showed that

in the wavy valley of transverse corrugated surface

the coolant jets ejected from adjacent holes were prone to interact each other

thus forming more coolant accumulation. Due to this feature

the adiabatic wall temperature on the wavy valley of transverse corrugated surface was relatively lower than that on the wavy peak. In general

reducing the hole diameter and enlarging the perforated percentage were illustrated to be significantly helpful to enhance the film cooling effectiveness under the same coolant usage for a given protected area

especially in the front developing zone of an effusion cooling scheme. Besides

the effusion holes arranged in a super-long-diamond mode where the streamwise hole-to-hole pitch was bigger than spanwise hole-to-hole pitch showed more favorable. However

the effect of spanwise-to-streamwise pitch ratio on the laterally-averaged adiabatic film cooling effectiveness was very weak at low blowing ratio.