Abstract
Interaction of a combustor and turbine in aircraft engines generates still a lot of open questions. Investigation of combustor and turbine separately have been done for a years by research institutes and aircraft engine companies, but there is lack of knowledge about the interaction effect. In the paper, numerical simulations results for combustor simulator and nozzle guide vane (NGV) of the first turbine stage are presented. No combustion is modelled, but the hot flow at the swirler inlet is applied. Geometry and flow conditions are defined according to the turbine stage designed for experimental investigations in FACTOR (Full Aerothermal Combustor-Turbine Interactions Research) project within a framework of European Commission 7th Framework Programme. The main objective of the presented investigations is an analysis of the location of the high temperature zone upstream of the nozzle guide vane and its effect on the wall temperature. Numerical simulations are carried out by means of Fine/Turbo Numeca with two turbulence models: Spalart-Allmaras and Explicit Algebraic Reynolds Stress Model. As a model validation, a comparison of total pressure, total temperature and flow angles downstream of combustor simulator with experimental data from University of Florence is also presented.
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