Numerical simulation of heat loaded aircraft engine turbine blade - internal cooling

The objective of this thesis was to show present the impact of the turbine blade cooling on blade material temperatures well as familiarize with processes and methods of numerical simulation by designing airfoil internal cooling system. The model of airfoil was created based on drawing print nr 17.41.0114 of engine Tumański R-11F2S-300. Geometry of all models described above is created using SIMENS NX4 program based on drawings obtained from available literature, and data acquired from the Internet. The discretization into a structural finite volume grid took place in commercial pre-processor GAMBIT registered trademark (GAMBIT and FLUENT – commercial CFD codes from Ansys Inc.). Conjugated heat transfer analysis was conducted in program FLUENTregistered trademark for four different cases, where the blade material properties were changed. The goal of this thesis was to obtain temperature fields and distribution in the turbine blade airfoil and to evaluate if applied cooling would be able to cool down this thermally loaded part. Calculated results show that proposed blade heat protection method is insufficient during steady state condition, mainly on the blade leading and trailing edge. In these two locations, the blade is overheated, and the high temperature level of applied material is unacceptable for used in jet engine turbine industry.