航空发动机主轴承热分析边界条件处理方法  被引量:3

Boundary Condition Processing Method of Aeroengine Main Bearing Thermoanalysis

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作  者:苏壮[1] 李国权[1] 

机构地区:[1]中航工业沈阳发动机设计研究所航空发动机动力传输航空科技重点实验室,沈阳110015

出  处:《航空发动机》2015年第3期72-76,共5页Aeroengine

基  金:航空动力基础研究项目资助

摘  要:为了提高航空发动机主推力球轴承热分析的计算精度,对轴承的摩擦发热和对流换热边界条件进行了分类及研究。应用ANSYS有限元分析软件,采用将摩擦热按体积生热率处理和将摩擦热按热流密度处理的2种不同方式,对边界条件进行了加载,分别对试验器状态的发动机主轴承进行了热分析计算,并与试验测量结果进行了对比。计算结果表明:采用表面效应单元加载热流密度的方式得到的轴承温度分布更理想,内部热点温度更集中,热点温度比按体积生热率加载的高。2种边界条件处理方法均已应用到航空发动机润滑系统热分析中,提高了航空发动机润滑系统热分析的准确性。In order to improve the thermoanalysis calculation accuracy of the aeroengine main thrust ball beating,the friction heat and convection heat transfer boundary condition of the aeroengine main bearing were classified and researched.By using ANSYS,two different methods were applied in managing the frictional heat with volumetric heat generation rate and with the heat flux,those two boundary conditions were loaded onto the main beating.The results of calculation indicate that the beating tem-perature distribution which obtained by loading heat flux on the surface effect element is better,the internal hot spots of temperature is more concentrate,and the temperature of internal hot spots is higher than that with loading heat generation on volume.Two methods were applied in the thermoanalysis of the aeroengine lubrication system,and the thermoanalysis accuracy of the aeroengine lubrication system was increased.

关 键 词:主轴承 热分析 边界条件 摩擦发热 对流换热 航空发动机 

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]

 

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