AXISYMMETRICAL INTERMEDIATE CASE PART INCLUDING AN INSERT POSITIONED IN AN ANNULAR GROOVE

摘要

The invention proposes an axisymmetrical portion (24) for an aircraft turbojet engine intermediate case intended to protrude downstream from an outer axisymmetrical portion of said intermediate case, the axisymmetrical portion (24) including an annular groove (40) radially open outwards, characterized in that it includes at least one insert (60) laid out inside the groove (40), which covers each internal face (50, 52, 54) of the groove (40) and which is radially open outwards.;The invention also proposes an insert intended to be mounted in the axisymmetrical portion and a method for mounting the insert in the axisymmetrical portion.

主权项

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, at least one insert laid out inside the groove, which covers each internal face of the groove and which is radially open outwards.