Patent ID: 7870740

Claim:
An afterbody for an aircraft turbojet engine comprising: an afterburner casing delimiting an afterburner duct; a liner for the thermal protection of the afterburner casing that is arranged radially to the inside with respect to this casing; and at least one diaphragm-forming assembly interposed between said thermal protection liner and said afterburner casing, the diaphragm-forming assembly defining a flow area which is traversed by a stream which ventilates the afterburner casing, wherein said thermal protection liner is mounted on said afterburner casing by fastening elements which impose an angular displacement on the thermal protection liner in a circumferential direction with respect to said casing when said liner expands under the effect of thermal stresses, wherein said diaphragm-forming assembly includes a first annular plate and a second annular plate which overlap each other, each of the first annular plate and the second annular plate is perforated with a plurality of apertures and is mounted on said afterburner casing and said thermal protection liner respectively, said apertures in the two annular plates jointly define said flow area, and wherein said diaphragm-forming assembly is designed such that the expansion of the thermal protection liner under the effect of thermal stresses causes a displacement of said second annular plate in said direction of angular displacement with respect to said first annular plate, leading to an increase in the size of said flow area defined by the apertures.