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.