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.

中文翻译：

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地面怠速条件下涡轮螺旋桨发动机短舱气流的 CFD 模型

本文研究的是新型涡桨发动机的舱室冷却。所考虑的发动机集成大大增加了前机舱室内的温度。为了在飞机在热浸回着陆后的所有运行状态和发动机/短舱状态下实现短舱内发动机部件的最佳温度条件，提出了一种新的机舱冷却系统。建议的冷却系统包括机舱前部的标准 NACA 进气口、前机舱舱后部的两组附加进气口、Zone1 和标准机舱间隙（排气口周围）以及整流罩间隙。给定多标准任务中的选型方法基于给定的发动机附件温度额定值。此外，由于结构原因，机舱前部的金属蒙皮和加强筋应保持在规定的温度限值以下。使用前短舱舱室的 3D CFD 模型，利用软件 ANSYS 分析该舱室。由制造商对所考虑的 ATP 型涡轮螺旋桨发动机进行基准测试，用于定义本研究中所有必要的边界条件。