航空制造技术
航空製造技術
항공제조기술
AERONAUTICAL MANUFACTURING TECHNOLOGY
2015年
11期
83-86
,共4页
王彬%黄继华%张田仓%季亚娟%何胜春
王彬%黃繼華%張田倉%季亞娟%何勝春
왕빈%황계화%장전창%계아연%하성춘
高温合金%惯性摩擦焊%界面温度%微观组织
高溫閤金%慣性摩抆銲%界麵溫度%微觀組織
고온합금%관성마찰한%계면온도%미관조직
Superalloy%Inertia friction welding%Interface temperature%Microstructure
对FGH96/GH4169异质高温合金惯性摩擦焊接头组织形貌及演变过程进行分析,测量了焊接过程的界面温度。结果表明,惯性摩擦焊近界面处最高温度超过1100℃,达到母材强化相固溶温度区间。摩擦初期GH4169侧率先产生磨损颗粒;摩擦过渡期磨损颗粒被细化,摩擦界面形成高温粘塑性金属,在顶锻压力作用下开始形成飞边,夹杂物随之被挤出;准平衡摩擦阶段界面处高温粘塑性金属被持续挤出,飞边增大。焊后于焊接界面处形成等轴细晶区,细晶区与母材间为热力影响区,产生明显的变形,形貌为拉长晶粒。
對FGH96/GH4169異質高溫閤金慣性摩抆銲接頭組織形貌及縯變過程進行分析,測量瞭銲接過程的界麵溫度。結果錶明,慣性摩抆銲近界麵處最高溫度超過1100℃,達到母材彊化相固溶溫度區間。摩抆初期GH4169側率先產生磨損顆粒;摩抆過渡期磨損顆粒被細化,摩抆界麵形成高溫粘塑性金屬,在頂鍛壓力作用下開始形成飛邊,夾雜物隨之被擠齣;準平衡摩抆階段界麵處高溫粘塑性金屬被持續擠齣,飛邊增大。銲後于銲接界麵處形成等軸細晶區,細晶區與母材間為熱力影響區,產生明顯的變形,形貌為拉長晶粒。
대FGH96/GH4169이질고온합금관성마찰한접두조직형모급연변과정진행분석,측량료한접과정적계면온도。결과표명,관성마찰한근계면처최고온도초과1100℃,체도모재강화상고용온도구간。마찰초기GH4169측솔선산생마손과립;마찰과도기마손과립피세화,마찰계면형성고온점소성금속,재정단압력작용하개시형성비변,협잡물수지피제출;준평형마찰계단계면처고온점소성금속피지속제출,비변증대。한후우한접계면처형성등축세정구,세정구여모재간위열력영향구,산생명현적변형,형모위랍장정립。
Inertia friction welding of FGH96/GH4169 superalloy is completed, and the interface tem-perature during the welding process is measured. The weld microstructure is observed and the evolution process is analyzed. The results show that the top temperature during the welding process exceeds 1100℃, and is higher than the solid solution temperature of strengthening phase. In the initial phase wear particles are easily generated in the side of GH4169 superalloy. Wear particles are thinned during the transition phase, high temperature plasticized layer and lfash are formed near the interface, and inclusions are ex-pelled from the rubbing interface. During the quasi stable phase plasticized metal continues moving outside. After welding the grains symmetry in the interface are reifned, and the grains a little far from the interface are apparently deformed and presents elongated feature.