CAJ | 학술논문

冲压进气冷却是目前控制战斗机发动机舱内温度分布的主要方式。利用基于模型的发动机性能分析方法，提供不同工况下发动机分段热壁边界条件，通过非结构化网格和k-ε湍流模型方法求解流动与传热控制方程，数值模拟了某型发动机舱在典型飞行状态和发动机工况下的流动特征及流场关键参数分布，并与试验结果进行了对比分析。结果表明，模拟结果与试验结果吻合良好，模拟方法能准确预测发动机舱温度场分布，为通风冷却系统和灭火系统的设计与优化提供依据。
충압진기냉각시목전공제전두궤발동궤창내온도분포적주요방식。이용기우모형적발동궤성능분석방법，제공불동공황하발동궤분단열벽변계조건，통과비결구화망격화k-ε단류모형방법구해류동여전열공제방정，수치모의료모형발동궤창재전형비행상태화발동궤공황하적류동특정급류장관건삼수분포，병여시험결과진행료대비분석。결과표명，모의결과여시험결과문합량호，모의방법능준학예측발동궤창온도장분포，위통풍냉각계통화멸화계통적설계여우화제공의거。
Ram air inlet cooling is the main way to control the fighter engine compartment temperature dis-tribution. Based on the model of the engine performance under different working conditions, engine block hot wall boundary conditions were provided. By means of the unstructured grid and k-ε turbulent model method, the flow and heat transfer control equations were solved. The flow characteristics of key parameters and flow field distribution of a certain type of engine compartment in a typical flight condition and engine working conditions were simulated and compared with the test results. The results show that the simulation results agree with test results and the method can accurately forecast engine compartment temperature field distribution that will provide a scientific basis for ventilation cooling system and fire extinguishing system design and optimization.