航空发动机主轴-轴承系统温度场分析  

Analysis on Temperature Field of Aircraft-Engine Mainshaft-Bearings System

作　　者：郑学普[1] 周彦伟[1] 邓四二[1] 杨海生[1] 孟瑾[1] 杜辉[1] 

机构地区：[1]河南科技大学机电工程学院,河南洛阳471039

出　　处：《河南科技大学学报（自然科学版）》2004年第1期30-33,共4页Journal of Henan University of Science And Technology:Natural Science

基　　金：国家"十五"科技攻关资助项目(HK-2002-043)

摘　　要：在对航空发动机主轴-轴承系统热力学分析基础上,对主轴-轴承系统的发热、传导、对流、辐射等进行了分析,利用热路网络热流量平衡原理,建立了相应的热平衡方程组,并用数值分析方法对系统温度场进行了数值求解。实例计算和试验测试结果对比分析表明:所选节点温度的计算值和实测值之间相差不足1.2%,反映出本文建立的航空发动机主轴-轴承系统温度场计算数学模型具有很高的精确度,完全适用于一般的主轴-轴承系统温度场理论计算与分析。On the basis of the thermodynamic analysis of the aero-engine mainshaft-bearing system, the characteristics of the mainshaft-bearing system such as generated-heat, conduction, convection, radiation etc are analysed, and the corresponding thermal balance equations based on the thermal flux balance principle for the route of thermal conduction are established. Moreover,the field of temperature in the system is calculated by means of numerical analysis method, and the calculation value is verified by test. The result of the experiment analysis shown that the mathematical model proposed in the paper for the temperature field calculation of the aero-engine mainshaft-bearing system has the high precision, and is used to calculate and analysis the temperature field of general mainshaft-bearings system.

关 键 词：航空发动机 主轴-轴承系统 温度场 热分析 

分 类 号：V233.45[航空宇航科学与技术—航空宇航推进理论与工程] V232.2