航空发动机涡轮前支承轴承腔油气两相物理场分析  

Physical Fields of Oil/Air Two-Phase in Aeroengine Bearing Chamber in front of Turbine

作　　者：孙恒超[1] 陈国定[1] 陈薄[1] 

机构地区：[1]西北工业大学机电学院,陕西西安710072

出　　处：《西北工业大学学报》2013年第1期71-76,共6页Journal of Northwestern Polytechnical University

基　　金：国家自然科学基金(50975233;51275411);西北工业大学研究生创业种子基金(Z2012051)资助

摘　　要：处在航空发动机热区的涡轮前支承轴承腔的油气两相物理场分析是进行二次流及润滑系统设计的重要基础工作。文章结合某型发动机涡轮前轴承腔的结构和工况参数,构建了适用于发动机全运行状态下的轴承腔油气两相物理场理论计算模型,求解获得了轴承腔内油气两相介质流动的物理场。探讨了轴承腔内油气两相流动的速度、压力、温度及壁面油膜厚度在腔内不同位置的分布情况;分析了发动机运行状态对上述物理场的影响规律;与试验数据的比较支持了文中理论分析方法的正确性。提出的轴承腔油气两相物理场分析方法对于航空发动机主轴支承轴承腔的润滑与换热设计具有应用价值。The analysis of physical fields of oil/air two-phase flow of in beating chamber in front of turbine and at hot zone of aeroengine is an important and basic work in designing lubrication and secondary air systems. According to the geometry and operating parameters of beating chamber equipped on a certain turbofan engine, a theoretical calculation model for analyzing oil/air physical fields in beating chamber for all operating states of aeroengine is built, the oil/air two-phase flow physical fields are obtained. The velocity, pressure, temperature and oil film thickness distributions of oil/air two-phase flow in bearing chamber are discussed. The effect of aeroengine operat- ing sates on physical fields is analyzed. The comparison of calculated values and experimental data supports the cor- rectness of the present theoretical methods. The theoretical methods for analyzing oil/air two-phase physical fields and the calculated results presented in this paper are, we believe, applicable to beating chamber lubrication and heat transfer engineering design and academic research.

关 键 词：航空发动机 轴承腔 两相流 物理场 对流换热 油膜厚度 

分 类 号：V233.4[航空宇航科学与技术—航空宇航推进理论与工程]