Inconel 718變形高溫合金熱加工組織演變與發展趨勢

Inconel 718變形高溫合金熱加工組織演變與發展趨勢MICROSTRUCTURE EVOLUTION OF INCONEL 718 SUPERALLOY DURING HOT WORKING AND ITS RECENT DEVELOPMENT TENDENCY

本文首先針對Inconel 718合金的鍛造工藝過程，較為系統地闡述了合金高溫變形時的再結晶機制、晶粒長大、δ相形態控制以及存在的殘余應力問題；基于選區激光熔化技術在航空發動機材料增材制造領域的潛在優勢和應用前景，分析了選區激光熔化技術制造Inconel 718合金凝固組織和性能的各向異性，探討了熱處理工藝在消除有害相、改變組織結構及力學行為等方面的重要作用和局限性；結合高溫服役過程的組織演變，分析了Inconel 718合金變形時涉及位錯滑移、孿生、γ″相剪切方式的變形機制；最后，介紹了通過調整Inconel 718合金成分來改變強化相結構，從而進一步提高變形高溫合金服役溫度的有效嘗試（如Allvac 718Plus合金的服役溫度提高了55 ℃），指出了通過成分調整來獲得熱穩定性優異的-復合析出結構是新型變形鎳基高溫合金的重要發展方向。

Here some critical issues existed during forging process of Inconel 718 disks involving recrystallization mechanisms, grain growth, δ-phase morphology control and residual stress are explained. Based on the potential application prospect of selective laser melting in additive manufacture of aerocraft engine components, the specialized anisotropic microstructure and mechanical performance resulted from the rapid solidification process in selective laser melting are analyzed. Furthermore, the importance and difficulty of heat treatment in eliminating Laves-phase as well as tailoring substructure and related mechanical behavior are also discussed. The deformation mechanisms of Inconel 718 alloy at high temperature are illustrated in detail, comprising of dislocation planar slip, twinning and dislocation-shearing γ″ precipitates in complex modes. At last, a newly developed wrought nickel superalloy (Allvac 718Plus, with a increase in service temperature of 55 ℃ as compared to that of Inconel 718) is introduced, and some recent progress aimed at modifying chemical compositions and phase compositions to improve service temperature on the basis of Inconel 718 alloy are also reviewed. The results indicate that the more stable γ″-γ′ composite structure is important for the further design of next-generation wrought nickel superalloys.

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