航空发动机用GH4738涡轮盘的模锻工艺研究

• 作 者: 毕中南 曲敬龙 邓群 喻伟雄 成晓鸣 董建新
• 机 构: 钢铁研究总院高温材料研究所,中国南方航空工业(集团)公司,中航工业航空动力机械研究所,北京科技大学,
• 出 处: 钢铁研究学报
• 发表日期: 2011年S2期
• 关键词: GH4738 航空发动机 GH4738合金 涡轮盘 模锻工艺 数值模拟 微观组织 锻件 锻造温度 模锻

基于GH4738合金热变形过程中的晶粒组织预测模型,对航空发动机用GH4738涡轮盘锻件的模锻全过程进行有限元模拟,并跟据实际锻件解剖分析结果进行验证。通过模拟分析锻造温度、模具温度以及成形方式对盘锻件组织的影响规律,给出了优化的模锻工艺。结果表明:为达到盘锻件的晶粒度要求,模锻温度不宜超过1100℃;对模具进行400℃预热可以有效减少冷模组织;采用镦饼+模锻的方式可以有效提高累计变形量,使晶粒更细化,分布更均匀。

Based on the prediction model of grain structure in the heat deformation process of GH4738 alloy, the finite element simulation of die forging process of GH4738 turbine disc forgings was performed in aeroengine, and the results were verified according to the actual analysis results of forgings. By analyzing the influence of forging temperature, mold temperature and forming method on the microstructure of disc forging, the optimal forging process was given. The results show that the die forging temperature should not exceed 1100 ℃ in order to meet the grain size requirement of plate forgings. The preheating of the die at 400 ℃ can effectively reduce the cold die structure. The use of upset cake + die forging can effectively increase the cumulative deformation, The grain refinement, distribution more uniform.