摘要
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。
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 blockhot wall boundary conditions were provided. By means of the unstructured grid and k-εturbulent modelmethod, the flow and heat transfer control equations were solved. The flow characteristics of key parametersand flow field distribution of a certain type of engine compartment in a typical flight condition and engineworking conditions were simulated and compared with the test results. The results show that the simulationresults agree with test results and the method can accurately forecast engine compartment temperature fielddistribution that will provide a scientific basis for ventilation cooling system and fire extinguishing systemdesign and optimization.
出处
《燃气涡轮试验与研究》
北大核心
2014年第5期38-42,共5页
Gas Turbine Experiment and Research
关键词
发动机舱
冲压进气
通风冷却系统
温度分布
发动机性能
数值模拟
engine compartment
ram-air inlet
ventilation cooling system
temperature distribution
engine performance
numerical simulation
