Abstract: A heat exchanger designed to be fixed to a turbomachine wall delimiting a gas flow stream, this exchanger including a body with a front face through which the gas flow passes; an attachment face to the wall; an external face opposite the attachment face and connected to the front face; two lateral faces connected to the front face; a cover surrounding the front face and extending along the prolongation of the external face and the lateral faces, to delimit an intake with an area smaller than the area of the front face, this intake being located upstream from the front face relative to the gas flow stream.

Abstract: An afterbody for a turbojet engine having a central axis, provided with a nozzle comprising two doors facing each other between two lateral beams. The doors pivot around axes defining a pivot direction, between a retracted position, in which a middle portion of the downstream edge of the doors forms the edge of the outlet section of the nozzle combined with the downstream edges of the two lateral beams, and a deployed position, in which the middle portions of the downstream edges of the pivoting doors come together so as to block the channel between the two lateral beams in order to reverse the thrust of the turbojet engine gases. The edge of the outlet section of the nozzle further having a crown of noise-reducing chevrons alternating with indentations and the afterbody.

Abstract: An afterbody for a turbojet engine having a central axis, provided with a nozzle comprising two doors mounted facing each other between two lateral beams pivoting around axes defining a pivot direction, between a retracted position, in which a middle portion of the downstream edge of said doors forms the edge of the outlet section of the nozzle combined with the downstream edges of the two lateral beams, and a deployed position, in which said middle portions of the downstream edges of the pivoting doors come together so as to block the channel between the two lateral beams in order to reverse the thrust of the turbojet engine gases, the edge of the outlet section of the nozzle further having a crown of noise-reducing chevrons alternating with indentations and the afterbody wherein each noise-reducing chevron formed on the middle portion of the downstream edge of a pivoting door is opposite an indentation in the middle portion of the other pivoting door in the direction perpendicular to said pivot direction, t

Abstract: The invention concerns an afterbody for a mixed-flow turbojet engine having a central axis (LL), comprising a lobed mixer (6), having alternating hot lobes (12) projecting into the secondary flow (F2) and cold lobes (13) penetrating into the primary flow (F1), and a nozzle (1) comprising, on the trailing edge (14) of same, longitudinal indentations (15) defining a crown of noise-reducing chevrons (7), characterised in that, at a predefined abscissa (X5) on the central axis (LL) downstream from the lobed mixer (6), the inner wall (2) of the nozzle (1) has a neck where the surface area of the transverse passage section of a flow into the nozzle passes through a minimum, and in that, downstream from this predefined abscissa (X5), the radius of the inner wall (2) of the nozzle (1) varies between the indentations (15) and the chevrons (7) so as to produce, in the flow, in the vicinity of said crown of chevrons (7), azimuth fluctuations of the Mach number.