Separated computation of the whole jet engine workflow

The research goal was the methodology to calculate gas turbine engine (GTE) workflows and in the compressor, in the combustion chamber and the turbine at the same time. Our method allows predicting interactions between components of a GTE. Solution is provided in separate solvers step by step. The results of modeling entire GTE in a different CFD codes are presented. Efforts to decide some problem of matching models are written. Author shows the maximum accuracy of boundary data achieved with this approach.