Effects of non-uniform inlet temperature distribution on air cooled gas turbine vane

Conjugate heat transfer numerical simulation was employed to aero engine high pressure guide vane with compound cooling techniques in this paper. Effects of non-uniform inlet temperature distributions on heat transfer of guide vane was investigated. The analyses showed that the non- uniform turbine inlet temperature distribution in radial direction could usually increase the heat load near the mid-span region on vane surface, and weaken the performance of downstream film cooling. The existence of combustor hot streak usually increased severer heat load on vane surface. The compound cooling techniques could effectively reduce the heat load which was caused by non-uniform turbine inlet temperature distribution.