AIRCRAFT TURBOMACHINE COMPRISING AN IMPROVED DEVICE FOR ATTACHING A PART TO THE WALL DELIMITING AN ANNULAR GAS CIRCULATION LINE

Abstract

The invention relates to an aircraft turbomachine comprising an annular duct (V3) delimited by a boundary wall (16) comprising a first aerodynamic surface (16a), as well as a second fixing surface (16b), the turbomachine also comprising a part (12) attached to the wall (16), against the second fixing surface (16b). According to the invention, a fastening device (20) comprises a recessed nut (22) including a first bearing surface (26), the boundary wall (16) of the groove including a through orifice (34) having a housing portion receiving the first bearing surface (26) of the nut (22) and opening onto the aerodynamic surface (16a), the device (20) including a screw head (44) arranged outside the groove (V3) and having a second bearing surface (46) against the part (12), the screw head (44) being equipped with a gripping surface (48) configured to cooperate with a tightening tool. Figure 2 for the abstract.