In order to evaluate the strong aerodynamic interactions between the secondary fan/OGV stage with the airframe engine integration system, and the ability of numerical methods to assess these interactions, several numerical methods have been tested. They range from RANS computation where the engine is modelled using simplified Boundary Conditions to full 360° URANS computations including the rotating fan blades. Intermediate methods such as Body-Force and Actuator Disk approaches have also been assessed. Computations were carried out on a generic configuration designed in the frame of the European ASPIRE project. The nacelle, short air intake and nozzle were designed by Airbus, the fan/OGV stage by DLR based on specifications provided by Airbus. This paper aims at presenting those results, including a grid convergence study, and at detailing the advantages and drawbacks of each method for two operating conditions: in cruise and at low speed. Nomenclature ADP = Aerodynamic Design Point LS = Low-Speed URANS = unsteady Reynolds Average Navier-Stokes AD = Actuator-Disk BF = Body-Force UP = Uniform Pressure AB = Abacus-based OGV = Outlet Guide Vane FPR = Fan Pressure Ratio BPR = By-Pass Ratio RNA = Blade number reduction (Réduction du Nombre d'Aubes in French)
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