| Citation: | YIN Huali, SHAN Yong, DENG Ming, et al. Ventilation and cooling test of the core nacelle for civil turbofan engine with large bypass ratio[J]. Journal of Aerospace Power, 2023, 38（6）：1350-1359 doi: 10.13224/j.cnki.jasp.20210614
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A full-scale large bypass ratio turbofan engine core nacelle ventilation and heat transfer test system was designed by changing the cooling air flow rate, the heat generation on the core casing surface and the core nacelle shell insulation to study the convective heat transfer characteristics in the cabin. The results showed that with the increase of intake air flow rate, the surface heat transfer coefficient of the core casing of each section increased accordingly. Due to the presence of high-level flanges in the front/rear compartments, the increase in the front compartment intake air flow rate had almost no influence on the convective heat transfer on the surface of the rear compartment casing. When the intake air flow rate reached 0.05 kg/s, the improvement of the cabin space temperature was limited. Spatially, the air flow temperature of the upper part of the front cabin was about 10 K higher than that of the lower part, and the rear cabin was about 20 K higher. At the same intake air flow rate, the heat output of the casing surface increased, and the surface heat transfer coefficient of the casing increased slightly, with a difference of about 10 W/（m2·K）. The existence of the insulation layer caused the heat transfer of the core casing to the environment through radiation heat exchange to decrease, and the heat transfer method mainly relied on convection heat transfer, so the surface heat transfer coefficient was relatively improved, with the difference about 60 W/（m2·K）. The empirical formulae of surface heat transfer for each section of the core casing were obtained by using the least squares method, which can be used as a reference for the design of ventilation and cooling engineering for the core nacelle with large bypass ratio turbofan.
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