Numerical Models Tuning Procedure: a General Method for Aircraft Cooled Components

In order to correctly simulate the fluid and thermal behavior of different aircraft components, the choice of the suitable numerical tools alone isn’t sufficient and so it must be combined with a good tuning procedure that, starting from the available experimental data, allows obtaining high accuracy numerical models. The authors in a previous work [1], to accomplish the tuning of a numerical model representing one stage of a LPT (Low Pressure Turbine), have identified and applied, with fairly good results, a calibration procedure, named Thermal Match. The aim of the present work is to perform a further validation of the pointed up methodology verifying, at the same time, how its use can be extended to others engine components. For this reason the tuning procedure has been applied to a stator blade, having in common with the LPT stage only the need to be cooled during the operation, but with completely different geometrical features and, in addition, numerically simulated by using others software.