Abstract: The invention relates to a turbojet engine nacelle component (23) cooling assembly (30), said assembly (30) comprising at least one composite wall (20) separating a cold zone (8) and a hot zone (16) containing said component (23), said assembly (30) comprising at least one opening (31) made in said composite wall (20) and a thermally conductive interface element (33) positioned on the composite wall (20) in such a way as to obstruct said opening or openings (31), said element (33) being intended to be associated with said component (23). The invention also relates to a nacelle comprising a component (23) that is intended to be cooled, and to such a cooling assembly (30).

Abstract: The invention relates to a method for installing heat shielding (31), including a heat cushion (33) covered with a ply (35a) made from a structural material, on a fixed internal structure (29) of a jet engine nacelle, including the following consecutive steps: spreading an adhesive (43) that guarantees good mechanical strength at high temperatures on at least one of the elements selected from said ply (35a) and an internal skin (39) of the fixed internal structure; applying said ply (35a) to said internal skin (39); and, if necessary, setting said adhesive (43).