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采用搅拌摩擦焊技术对航空发动机静电传感器的钛合金外壳进行封装。首先建立了焊接过程中的热输入数学模型,将模型应用于焊接过程中整体温度场仿真,并通过试验对有限元模拟结果进行验证。结果表明,随着焊接过程的进行,工件表面温度高的区域逐渐扩大,搅拌头所处位置始终是温度最高的区域,并呈现出前窄后宽的半椭圆形状;工件内部的温度分布可由金相组织结构来分析,金相组织结构变化大的区域为热机影响区,工件瞬间温度升高,并随着热源影响的减小温度逐渐降低,为航空发动机静电传感器的封装提供了指导依据。
Friction stir welding technology is used to encapsulate the aero-engine electrostatic sensor’s titanium alloy shell. Firstly, a mathematical model of heat input during welding is established. The model is applied to the simulation of the whole temperature field in the welding process. The results of the finite element simulation are validated through experiments. The results show that as the welding process progresses, the area with high temperature on the surface of the workpiece gradually expands, and the position of the stirring head is always the area with the highest temperature, showing a semiellipsoid shape with narrow front and back width. The temperature distribution inside the workpiece can be determined by metallographic According to the analysis of the microstructures, the area with large changes in the microstructure of the microstructure is the heat affected zone. The instantaneous temperature of the workpiece increases and decreases with the decrease of the heat source temperature. This provides a basis for the encapsulation of the electrostatic sensor of aeroengine.