摘要
针对航空发动机SiC_(f)/SiC-高温合金热端部件的连接,研发了一种Ni基高熵钎料,并研究了钎焊温度对SiC_(f)/SiC-GH4950高温合金接头界面组织和力学性能的影响。结果表明,SiC_(f)/SiC-GH4950接头的典型界面组织为SiC_(f)/SiC/(Ni,Co)_(2) Si+石墨/Cr_(3)C_(2)+(Ti,W,Cr)C_(1-x)/Co-Cr-Ni-W-Si-Ti+(Ni,Co)_(3)(Al,Si)+(Ni,Co)_(3)(Si,Ti)/GH4950。在1220℃保温10 min的条件下,SiC_(f)/SiC-GH4950接头的室温强度和1000℃下的高温强度分别为158 MPa和66.3 MPa,接头主要断裂于(Ni,Co)_(2) Si+石墨的薄弱区域。
A Ni-based high-entropy filler was developed for the joining of SiC_(f)/SiC ceramic-matrix composites and superalloy hot-end components in aero-engines,and the effect of brazing temperature on the interface microstructure and mechanical properties of SiC_(f)/SiC-GH4950 superalloy joints was studied.The results indicate that the typical interfacial microstructure of the SiC_(f)/SiC-GH4950 joint is SiC_(f)/SiC/(Ni,Co)_(2) Si+graphite/Cr_(3)C_(2)+(Ti,W,Cr)C_(1-x)/Co-Cr-Ni-W-Si-Ti+(Ni,Co)_(3)(Al,Si)+(Ni,Co)_(3)(Si,Ti)/GH4950.Under the condition of holding at 1220℃for 10 min,the room temperature strength and high-temperature strength at 1000℃of the SiC_(f)/SiC-GH4950 joint were 158 MPa and 66.3 MPa,respectively.The SiC_(f)/SiC-GH4950 joint mainly fractured along the weak zone of(Ni,Co)_(2) Si+graphite.
作者
陈修凯
陶军
卞红
宋晓国
侯金保
吕彦龙
CHEN Xiukai;TAO Jun;BIAN Hong;SONG Xiaoguo;HOU Jinbao;LÜYanlong(Aeronautical Key Laboratory for Welding and Joining Technologies,AVIC Manufacturing Technology Institute,Beijing 100024,China;State Key Laboratory of Precision Welding&Joining of Materials and Structures,Harbin Institute of Technology,Harbin 150001,China;Shandong Provincial Key Laboratory of Special Welding Technology,Harbin Institute of Technology(Weihai),Weihai 264209,China)
出处
《航空制造技术》
北大核心
2026年第3期101-108,共8页
Aeronautical Manufacturing Technology
基金
国家科技重大专项(J2022-Ⅶ-0003-0045)。
