Numerical Study of the Combustor - Turbine Interaction Using Coupled Unsteady Solvers

The aero-thermal design of high pressure turbinesis generally performed by using uniform total inlet conditions. For turbines operating with modern combustion chambers such a simplified approach is not sufficient anymore, and the necessity of studying both components at the same time clearly comes out for more accurate results. The aim of the present work is to bypass the stability problems by coupling a reactive compressible pressure-based solver for the combustion chamber to a compressible density -based solver developed for turbines. The coupling procedure is tested on solvers based on unsteady algorithms, and applied to a configuration representative of a real engine.