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针对航空飞机上应用的具有管板接头结构的散热器,利用ANSYS软件,建立二维模型,对1Cr18Ni9Ti不锈钢散热器分别按“直接加热”和“分阶段加热”两种电子束钎焊工艺钎焊的温度场和应力场进行了有限元分析。结果表明,采用分阶段加热钎焊工艺时,获得了均匀的钎焊面温度分布,钎焊面大部分区域的温度在1042～1051℃之间,且在钎焊温度范围之内;对于径向残余应力,采用直接加热钎焊时,钎焊面上出现明显的应力集中区域,而采用分阶段加热钎焊,钎焊面上没有应力集中区出现;对于周向残余应力,分阶段加热钎焊的拉应力峰值较直接加热钎焊减小了11.2%;两种钎焊工艺的周向残余应力的拉应力峰值都大于径向残余应力的拉应力峰值,说明钎焊面的危险部位沿圆周方向。
Aimed at the radiator with tube-plate joint structure applied on aviation aircraft, the two-dimensional model was established by using ANSYS software. The two kinds of electron beam brazing furnaces were respectively heated by “direct heating” and “heating in stages” for 1Cr18Ni9Ti stainless steel radiator Finite element analysis of temperature and stress field of brazing process was carried out. The results show that the uniform brazing surface temperature distribution is obtained when the brazing process is staged. The temperature in most of the brazing surfaces is between 1042 and 1051 ℃ and within the brazing temperature range. For the radial Residual stress, the use of direct heating brazing, brazing surface obvious stress concentration area, and the use of brazing step by step brazing, brazing surface no stress concentration zone appears; for the circumferential residual stress, brazing stage by stage The tensile stress peak value of the circumferential residual stress in both brazing processes is larger than the tensile stress peak value of the radial residual stress, indicating that the dangerous parts of the brazing surface along the circumferential direction .