摘要
通过分析飞机发动机短舱的结构特点,发展了短舱空间温度分布的一维和三维数值计算方法。针对某型涡扇发动机的几种飞行状态,确立了其短舱流动和换热的计算模型,数值模拟了发动机短舱内的温度分布,并对计算结果进行了比较和分析。从计算结果可以看出,沿轴向短舱内的温度分布规律几乎与涡扇发动机沿轴向的温度分布规律是一致的。因此,若保证短舱内的温度不超温,必须降低涡扇发动机向短舱内的热传递,特别是涡扇发动机高温部件向短舱内的传热。
One-dimensional and three-dimensional numerical calculation methods for temperature distribution of nacelle space are developed through analyzing the structural features of aircraft engine na-celle.Aiming at several flight status of one turbofan a computational model for its nacelle flow and heat transfer is established and the temperature distribution inside the engine nacelle is simulated numerically,which results are compared and analyzed.The results show temperature distribution axially of the entine na-celle is almost consistent with turbofan engine axially.Therefore,it is essential to ensure the temperature of nacelle does not exceed the limit and reduce heat transfer from turbofan engine to the nacelle,especially from the high-temperature components.
出处
《机械设计与制造》
北大核心
2012年第2期32-34,共3页
Machinery Design & Manufacture
基金
航空科学基金(2008ZB53012)
关键词
发动机短舱
温度分布
对流
传热
Engine nacelle
Temperature distribution
Convection
Heat transfer
