The objective of this study is to propose a novel methodology to pursue the integrated, contextual simulation of the combustor and the first nozzle guiding vane of a jet engine, which can be usefully and efficiently employed also within design procedures. In common modeling practice, combustion chamber and high-pressure turbine are considered independently from one another, however fundamental experimental evidence shows that outflow conditions sensibly affect swirling flows in simplified geometries.
The investigation of the complex flow interactions occurring between combustion chamber outflow and turbine nozzle guiding vanes in gas turbines has been the subject of numerous studies in the last decade.
