航空发动机涡轮轴穿轧一体化成形工艺及其数值模拟与分析

Piercing-rolling integrated forming process of aero-engine turbine shaft and its numerical simulation and analysis

为解决航空涡轮轴成形难、制造流程长、材料利用率低等问题,提出了一种穿轧一体化成形工艺,运用多辊系斜轧技术,在外表面加工上克服阶梯状大断面收缩率的制造难题,在内孔加工上实现由减材制造到等材制造的转变.采用Simufact有限元软件对镍基高温合金GH4169涡轮轴坯的成形过程进行数值模拟,分析其成形过程中轧件金属流动以及应力应变场、力能参数的变化规律,验证了新工艺的可行性.

To solve the problems of difficult forming,long process,and low material utilization of aviation turbine shafts,a piercing and rolling integrated forming method is proposed,which utilizes multi roll diagonal rolling technology to overcome the manufacturing problem of stepped large section shrinkage in outer surface processing and achieve a transformation from reduced material manufacturing to equal material manufacturing in inner hole processing.The forming process of nickel based high-temperature alloy GH4169 turbine shaft blank was numerically simulated using simulation finite element software.The metal flow law of the rolled piece during the forming process,as well as the changes in stress-strain field and force energy parameters,were analyzed.The feasibility of the new process was verified,providing theoretical support for the research of the new process.