Metodi di progetto per la ricostruzione approssimata delle temperature nei dischi di turbina aeronautica

The present paper suggests a method to create a simplified algorithm to calculate temperature distribution on a turbine disk. The algorithm must be simple enough to be installed on the aircraft CPU, in order to compute disk life consumption in real time. The algorithm is based on Guyan reduction of a thermal finite element model of the disk. Unknown parameters in the final relationship have been calculated by minimizing the error function made with exact temperatures from a finite element analysis. The algorithm has been tested on boundary condition different from that used to compute unknown parameters