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


    Access

    Download


    Export, share and cite



    Title :

    CFD Model of Turboprop Engine Nacelle Airflow for Ground Idle Condition


    Contributors:


    Publication date :

    2022




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    Unknown




    An axisymmetric nacelle and turboprop inlet analysis including powersimulation

    GOLDEN, D. P. / BARBER, T. J. / CHIN, W. C. | AIAA | 1983


    Engine condition monitoring on small single engine turboprop

    Šplíchal, Miroslav / Červenka, Miroslav / Juracka, Jaroslav | Emerald Group Publishing | 2023

    Free access



    Analysis of Mach Number 0.8 Turboprop Slipstream Wing/Nacelle Interactions

    H. R. Welge / D. H. Neuhart / J. A. Dahlin | NTIS | 1981