Abstract: The invention relates to a mixer (100) for a separate-stream nozzle of a turbojet, the mixer being designed to mix a hot inner stream from the combustion chamber of the turbojet with a cold outer stream from the fan of the turbojet. The mixer comprises an inner shroud (120) defining a flow channel for said hot inner stream, an outer shroud (110) disposed around the inner shroud (120) and co-operating therewith to define a flow channel for said cold outer stream, and a lobed structure (130) having lobes (1321, 1322) extending longitudinally from the trailing edges (110a, 120a) of said shrouds. The lobed structure (130) is made of a ceramic matrix composite material and is attached to the outer shroud (110) by flexible fastener tabs (140).

Abstract: The invention relates to an exhaust system (100) for channeling the streams from a by-pass gas turbine, the system comprising a stream channeling nozzle and an exhaust casing (110) for connecting the channeling nozzle to the outlet of the gas turbine, said channeling nozzle comprising a primary nozzle (120) fastened to the exhaust casing (110) and a secondary nozzle (130) placed around the primary nozzle. The exhaust system further comprises means for fastening the secondary nozzle (130) directly to the exhaust casing (110), said secondary nozzle being supported by the exhaust casing independently of the primary nozzle (120).

Abstract: The invention relates to an exhaust system (100) for channeling the streams from a by-pass gas turbine, the system comprising a stream channeling nozzle and an exhaust casing (110) for connecting the channeling nozzle to the outlet of the gas turbine, said channeling nozzle comprising a primary nozzle (120) fastened to the exhaust casing (110) and a secondary nozzle (130) placed around the primary nozzle. The exhaust system further comprises means for fastening the secondary nozzle (130) directly to the exhaust casing (110), said secondary nozzle being supported by the exhaust casing independently of the primary nozzle (120).

Abstract: The invention relates to a mixer (100) for a separate-stream nozzle of a turbojet, the mixer being designed to mix a hot inner stream from the combustion chamber of the turbojet with a cold outer stream from the fan of the turbojet. The mixer comprises an inner shroud (120) defining a flow channel for said hot inner stream, an outer shroud (110) disposed around the inner shroud (120) and co-operating therewith to define a flow channel for said cold outer stream, and a lobed structure (130) having lobes (1321, 1322) extending longitudinally from the trailing edges (110a, 120a) of said shrouds. The lobed structure (130) is made of a ceramic matrix composite material and is attached to the outer shroud (110) by flexible fastener tabs (140).

Abstract: A mixer for a separate-stream turbojet nozzle, the mixer comprising along a longitudinal axis (X-X?) both a fastener shroud (10) for connecting said mixer to the exhaust casing of the nozzle, and a lobe structure (20) presenting a succession of inner and outer lobes (22 and 21) distributed circumferentially around the longitudinal axis (X-X?) of the mixer. The lobe structure (20) is made of a ceramic matrix composite material and further comprises a stiffener ring (30) that forms a connection between at least some of the lobes of said structure. Thus, the major portion of the mixer, i.e. the lobe structure, is made of a ceramic matrix composite material, thereby significantly reducing the weight of the mixer, and consequently reducing the weight of the nozzle.

Abstract: A mixer for a separate-stream turbojet nozzle, the mixer comprising along a longitudinal axis (X-X?) both a fastener shroud (10) for connecting said mixer to the exhaust casing of the nozzle, and a lobe structure (20) presenting a succession of inner and outer lobes (22 and 21) distributed circumferentially around the longitudinal axis (X-X?) of the mixer. The lobe structure (20) is made of a ceramic matrix composite material and further comprises a stiffener ring (30) that forms a connection between at least some of the lobes of said structure. Thus, the major portion of the mixer, i.e. the lobe structure, is made of a ceramic matrix composite material, thereby significantly reducing the weight of the mixer, and consequently reducing the weight of the nozzle.