某型弹用发动机前轴承腔耦合传热分析  

Coupled Thermal Analysis of a Certain Missile Engine's Bearing Chamber

作　　者：董广胜 刘振德[1] 李宛蓉[1] 

机构地区：[1]北京动力机械研究所,北京100074

出　　处：《战术导弹技术》2014年第5期63-69,共7页Tactical Missile Technology

摘　　要：给出了轴承腔的三维耦合传热分析方法,建立了某型发动机前轴承腔计算模型,利用ANSYS CFX软件对计算模型进行了耦合传热分析,并采用多相流模型模拟腔内复杂的油气流动。计算得到了某工况下轴承腔的温度场及流体域的流动参数,结果表明轴承腔固体结构件的温度及滑油温度均满足使用要求。所得结果与发动机试验测量值误差较小,轴承腔耦合传热分析方法实用可靠。The three-dimensional coupled thermal analysis method is put forward and a calculation model for the front bearing chamber of a certain engine is established. After that, coupled thermal analysis for the calculation model is done by ANSYS CFX. The complex air-oil flow in the chamber is simulated with muhiphase model. The bearing chamber＇ s temperature field and flow parameters in fluid domain are calculated with a certain operating condition. The results show that both the temperature of solid structure and oil meet the requirements. The error between the calculated results and the engine＇ s test values is quite small. The method used in this analysis is practical and reliable.

关 键 词：发动机 轴承腔 耦合热分析 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]