GH2674合金大型涡轮盘锻造成形技术
Forging Forming Technology of GH2674 Alloy Large Turbine Discs
赵兴东1, 崔树森1, 李殿国2, 马天军3
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作者单位：（1. 沈阳黎明航空发动机（集团）有限责任公司, 辽宁 沈阳 110043; 2. 钢铁研究总院， 北京 100081；3. 宝钢股份特殊钢分公司， 上海 200940）
中文关键字：GH2674; 涡轮盘; 锻造成形; 热模拟试验; 有限元模拟
英文关键字：GH2674; turbine disk; forging; isothermal compression test; finite element method
中文摘要：通过热模拟压缩试验研究了变形温度和变形速率对GH2674合金组织和性能影响，试验温度范围为950～1200 ℃，应变速率为0.01、0.05、0.1和1.0 s-1，变形量为65%；同时采用有限元法模拟分析了GH2674合金大型涡轮盘的成形过程，创造性的提出局部成形的方法，并对局部成形过程中应变场及载荷分布情况进行分析，从而确定了GH2674合金大型盘件合适的热成形工艺，并生产出了符合标准要求的直径达?准2200 mm的GH2674合金大型涡轮盘锻件。
英文摘要：The effects of deformation temperature and deformation rate on the microstructure and properties of GH2674 alloy were investigated using compression tests. The experiments were conducted at 950～1200 ℃, strain rates of 0.01, 0.05, 0.1 and 1.0 s-1 and reductions of 65%. In addition, a new forging process for turbine disk, named as partitioning forging, was simulated using FEM. By analyzing the simulation results, the deformation characteristics of partitioning forging, and the strain fields of GH2674, a suitable hot-forming process for GH2674 alloy was obtained and the large turbine disk with ?准2200 mm was successfully produced by the partitioning forging technology.