摘要
针对航空发动机涡轮热端部件的焊接制造需求,开展了定向凝固高温合金IC10的大间隙钎焊工艺研究。结果表明,采用Ni-Nb-W-Co-Cr-Al合金钎料在不同间隙内预填高温合金粉末,在1225℃/30 min钎焊条件下可获得冶金质量良好的IC10合金大间隙钎焊接头。当钎焊间隙为0.2 mm时,接头在980℃/75 MPa下的平均持久寿命为44.56 h,随钎焊间隙增大,接头高温持久寿命逐渐下降。从接头断口分析来看,接头中的脆性化合物相为薄弱相,易萌生裂纹,从而诱发断裂。
Focus on the requirements of aero-engine turbine guide vane manufacturing,the joining of directionally solidified IC10 superalloy was studied.The results show that,when using Ni-Nb-W-Co-Cr-Al based filler alloy,combined with superalloy power pre-filled into the brazing seam,the IC10 joints with good quality can be obtained under the brazing condition of 1225℃/30 min.With the thickness of brazing seam of 0.2 mm,the average creep rupture life can reach up to 44.56 h at 980℃/75 MPa.As the brazing gap increases,creep rupture life of the joint gradually decreased.According to the fracture of the joint after creep rupture test,it can be seen that the brittle phases within the joint was the weak link,and the crack easily initiated from these phases.
作者
邱嘉玉
丁宁
张元伟
毛唯
任新宇
QIU Jiayu;DING Ning;ZHANG Yuanwei;MAO Wei;REN Xinyu(AECC Beijing Institute of Aeronautical Materials,Beijing 100095,China;The Sixth Military Representative Office of the Air Force Equipment Department in Beijing,Beijing 101300,China)
出处
《航空制造技术》
CSCD
北大核心
2024年第12期58-62,共5页
Aeronautical Manufacturing Technology
基金
国家自然科学基金(52201050)。
