Patent ID: 8919136

Claim:
An after-body assembly for an aeroengine, the assembly comprising, along an axial direction: an annular part made of metallic material secured to the aeroengine; and an after-body part made of ceramic matrix composite material presenting the form of a body of revolution at least in an upstream portion of the after-body part, the after-body part being mounted on the annular part by resiliently flexible fastener tabs, each resiliently flexible fastener tab having a first end fastened to the annular part and a second end fastened to the upstream portion of the after-body part, wherein each resiliently flexible fastener tab includes an axial abutment portion and a radial abutment portion, the axial abutment portion extending radially from the second end of the resiliently flexible fastener tab and disposed to face the first end of the resiliently flexible fastener tab along the axial direction, the radial abutment portion disposed at the second end of the resiliently flexible fastener tab and configured to overly the first end of the resiliently flexible fastener tab along a radial direction.