航空发动机轴承—支承结构系统产热计算与分析  

Calculation and analysis of heat generation of aero-engine bearing-support system

作　　者：孙鹏 慕琴琴[1] 陈永辉[1] 燕群[1] SUN Peng;MU Qinqin;CHEN Yonghui;YAN Qun(National Key Laboratory of Strength and Structural Integrity,Aircraft Strength Research Institute of China,Xi’an 710065,China)

机构地区：[1]中国飞机强度研究所强度与结构完整性全国重点实验室,西安710065

出　　处：《航空工程进展》2024年第5期191-198,共8页Advances in Aeronautical Science and Engineering

基　　金：国家科技重大专项(J2019-Ⅳ-0010-0078,2017-Ⅶ-0011)。

摘　　要：开展轴承—支承结构系统的热源分析与产热量量化计算,能够为轴承腔热防护设计提供可靠依据。通过传热学、摩擦学等理论分析,建立航空发动机轴承—支承结构系统产热分析模型,开展轴承—支承结构的一维流热耦合计算,对航空发动机压气机和涡轮的中介承力框架进行产热量分析,评估巡航工况下不同热源对轴承—支承结构系统产热量的影响。结果表明:压气机中介支承结构右侧框架的壁面温度沿径向向上增加1.73%;由于主流道与盘腔之间存在级间封严,对流传热系数沿径向向上增大20倍,产热量占比最高的热源为支承结构壁面传热、轴承生热和密封装置生热;轴承—支承结构内的密封装置生热量在压气机中介承力框架内占比29%,在涡轮中介承力框架内占比35%。The heat source analysis and quantitative calculation of heat production of the bearing-support structure system can provide a reliable basis for the thermal protection design of the bearing cavity.Through theoretical analy-sis of heat transfer and tribology,a heat generation analysis model for the bearing-support system of an aircraft en-gine is established.1D thermal-fluid coupling calculations of the bearing-support system are carried.The intermedi-ate bearing support frames of the aero-engine compressor and turbine are analyzed for heat generation separately to evaluate the effects of different heat sources on the heat generation of the bearing-support system under cruise oper-ating conditions.The results show that the wall temperature of the right frame of the compressor intermediate sup-port system increases radially upward by 1.73%.The heat transfer coefficient(HTC)increases radially upward by 20 times due to the presence of interstage sealing between the main flow path and the disk cavity.Among them,the heat sources with the highest percentage of heat generation are through the support walls,bearings,and seals,and heat generation by the seals in the bearing-support system accounts for 29%in the intermediate bearing support frame of the compressor and 35%in the intermediate bearing support frame of the turbine.

关 键 词：轴承—支承结构 密封 空气系统 热分析 热计算 

分 类 号：V233[航空宇航科学与技术—航空宇航推进理论与工程]