Heat condition estimation of a high pressure turbine blade based on three dimensional modeling

Heat condition estimation methodology of cooled turbine blades with taking into account three dimensional and unsteady effects is presented. This methodology consists of two steps of numerical analysis. The first step is stator rotor interaction modeling in the investigated turbine stage and the second one is gasdynamic calculation applying conjugate heat transfer approach. Comparison of numerical results and experimental data of temperature distribution in the investigated blade was carried out. The experimental data were collected by thermocouples and thermocrystals gauges during tests of the engine core. Good agreement between numerical results and experimental data has been obtained. Gas segregation process in the blade passage was investigated. It was shown that unsteady effects lead to increasing adiabatic wall temperature as on the pressure as on the suction blade sides. Maximal influence of gas segregation is located in such areas where radial and secondary flows are weak. Conjugate heat transfer approach allows performing detail analysis of film cooling effectiveness according to cooling air concentration near the blade wall, revealing problem zones on the investigated blade as in the inner cavities as on the outer walls, obtaining threedimensional temperature distribution in the blade metal.