CFD Model of Turboprop Engine Nacelle Airflow for Ground Idle Condition

Research in this paper is concerned on bay cooling of the new type turboprop engine. The considered engine integration substantially increases temperature inside front nacelle compartment. In order to achieve optimal conditions for parts all operating regimes and engine/nacelle regime after aircraft landing at heat soak-back, a system proposed. Proposed consists standard NACA inlets nacelle, two additional groups gills rear part compartment, Zone1, gaps (around exhausts), plus spinner gap. sizing approach given multicriteria task based ratings accessories. Moreover, structural reasons, metal skin stiffeners should be maintained below defined limits. Using 3D CFD model compartment analysed, utilizing software ANSYS. benchmark testing ATP type, performed by manufacturer, used defining necessary boundary research.