Patent ID: 9677425
Date: 2017-06-13
CPC Classifications: F01D,F02K,F05D,Y10T

Claim:
1. An axisymmetrical portion for an aircraft turbojet engine intermediate case which extends downstream from said intermediate case, the axisymmetrical portion comprising: an annular groove radially open outwards, the groove including an axisymmetric front face, an axisymmetric rear face facing the front face, and a cylindrical bottom face connecting the front and rear faces at internal radial ends thereof; and an insert laid out inside the groove, the insert including a front wing, a back wing, and a bottom wall connecting the front and back wings, which respectively abut and cover the front face, the rear face, and the bottom face of the groove, and the insert is radially open outwards, wherein an outer shape of the insert matches a shape of the groove, wherein a shape of the front face and a shape of the rear face are different from each other such that the groove is not symmetric relative to a middle radial plane of the groove, wherein at least one of the front face, the rear face, and the bottom wall of the insert includes a rib which is received in a complementary throat provided in the axisymmetric portion, and wherein a material of the insert is more wear resistant than a material of the axisymmetrical portion including the groove.