摘要
用热模锻技术成功锻制出我国目前最大推力的航空发动机压气机用φ437 mm GH4169合金直接时效盘件。通过光学金相检验、室温和650℃拉伸试验、650℃/700 MPa组合持久及595℃/825 MPa蠕变试验对比研究了该盘件与普通盘件的组织和性能。结果表明:热模锻技术成功克服了模具的激冷影响,极大的改善了盘件的表面组织,获得了尺寸精化、组织均匀的盘件,该盘件的组织性能全部超过了该发动机的技术要求。与普通模锻工艺相比,热模锻工艺的单件节材35 kg,材料利用率提高30%左右,且工艺的可控性和稳定性更好。
China's largest aero-engine compressor thrust φ437 mm GH4169 alloy direct-aged compressor disk was success forged by hot-die forging technical. By optical metallographic examination, room temperature and 650 tensile ℃test, 650 ℃/700 MPa stress-ruptures and 595℃/825 MPa creep test, the microstructures and properties of the compressor disk have been investigated in this paper. The results showed that: The chill effect of the forging die has been overcome by hot-die forging techniques leading to the disk size pieces more refined and microstructures is more uniform. Microstructures and properties of the compressor disk are beyond the engine's technical requirements. Comparing with ordinary-die forging process, the material utilization ratio enhances about 30%. Meanwhile, this hot-die forging technology is more stable and can be more controlled.
出处
《钢铁研究学报》
CAS
CSCD
北大核心
2011年第S2期193-196,共4页
Journal of Iron and Steel Research
关键词
GH4169合金
热模锻
组织与性能
GH4169 alloy
hot-die forging
microstructures and properties
