Abstract: The invention relates to an aircraft engine assembly, comprising a turboshaft engine with a propeller as well as an attachment pylon (14) intended to be laterally attached on a rear portion of the structure of the aircraft, the pylon having an outer surface (20) forming an aerodynamic profile incorporating a trailing edge (21), the latter being arranged upstream of the propeller of the turboshaft engine. According to the invention, the pylon comprises a mobile rear flap (24) at least partially defining the trailing edge (21), as well as a control means (34) of the flap designed to steer the incidence of the latter, according to a law depending on the incidence of the aircraft.

Abstract: According to the invention, the shape of each of said chevrons is defined: by two lateral sides (21, 22) having front ends (21A, 22A) that are connected to said nozzle (4, 10) and that, when moving away from the latter, converge towards each other without joining so that the rear ends (21R, 22R) of said lateral walls (21, 22) are spaced from each other; and by a curvilinear transverse line (23.1) connecting the rear ends (21R, 22R) of said lateral walls (21, 22) by forming two rounded side protrusions (24.1, 25.1) separated by an intermediate rounded recess (26.1).

Abstract: An aircraft recovers the energy of conditioned air as it passes from a conditioned zone to outside the aircraft and uses the recovered energy to air condition the aircraft.

Abstract: Method for improving the performance of a bypass turbojet engine. According to the invention, the area of the annular outlet orifice (6) for the cold stream (9) is tailored to suit a reference value of the expansion ratio of said cold stream (9) which ranges between the extreme values of said expansion ratio corresponding respectively to the start and end of the phase of cruising flight.

Abstract: According to the invention, the hot flow nozzle includes a single skin (14s) conformed for promoting the cold flow (10) circulation when the aircraft including said turboshaft engine in a cruise flight mode.

Abstract: The invention relates to a method for reducing the noise missions from the rear of a turbo engine, and a turbo engine improved by said method. According to the invention, the nozzle for the cold flow (9) is modified by a transverse expansion and a lengthening thereof such as to be able to increase the length of the acoustic damping coating (14) supported on the inside of said nozzle.

Abstract: The arrangement of the invention includes mobile means for blocking an air passage channel (10) which are controlled by an aerodynamic surface (20) provided in said air passage channel (10) and capable of generating a lift force (P) under the action of the external air flow (F) flowing through said air passage channel (10).

Abstract: A turboengine that reduces rear noise emissions has a thickness of a rear part of a sound-attenuating coating, which is borne internally by an external fan cowl, that is increased toward a front part of the sound-attenuating coating. An increased-thickness zone is connected to a pan of the coating, located in a critical area of a jet nozzle, by a surface having a curved profile.

Abstract: The invention concerns an arrangement comprising at least one air passage channel (12) with an air vent (14), and designed to ventilate at least one confined zone (11) in an aircraft with fresh air entering upstream, through the air vent, in the channel and exiting downstream thereof towards the zone to be ventilated. The invention is characterized in that the cross-section of the air passage channel (12) is adjustable based on the speed and the altitude of the aircraft and the arrangement comprises therefor a membrane (19) elastically deformable under the action of a fluid control (18) to enable said channel cross-section to be varied.

Abstract: The invention concerns a ventilating air intake arrangement with mobile sealing device. The arrangement comprises at least one air passage channel (12) with an air vent (14), and is designed to ventilate at least one confined zone (11) in an aircraft with fresh air entering upstream, through the air vent, in the channel and exiting downstream thereof towards the zone to be ventilated. The invention is characterized in that the cross-section of the air passage channel (12) is automatically adjustable based on the speed and the altitude of the aircraft and the arrangement comprises therefor controllable mobile-element closing means (17) associated with the channel and for varying its cross-section.

Abstract: According to the invention, there is arranged on the inner fan cowl (13), in the vicinity of the nozzle throat (15) but to the rear thereof, a projecting annular boss (20) of rounded cross section which is able to locally change the speed of the cold stream (9) from the subsonic range to the supersonic range.

Abstract: The invention concerns a precooler (30) having an annular cross-sectional shape about the axis (L-L) of the pod and arranged inside the rear part (10R) of the inner shroud (10) in external contact with the cold flow (9) exiting the fan duct channel (13) and in close contract with the cooling air stream (29) drawn from said cold flow (9).

Abstract: The invention concerns a precooler (30) having an annular cross-sectional shape about the axis (L-L) of the pod and arranged inside the rear part (10R) of the inner shroud (10) in contact with a cold fluid (9) exiting the fan duct (13).

Abstract: The invention relates to a method of reducing noise emissions at the rear of a turboshaft engine and to a turboshaft engine thus improved. According to the invention, the thickness of the rear part (9R) of the sound-attenuating coating which is borne internally by the external fan cowl (10) is increased toward the front part (9A) thereof, and the increased-thickness zone (18) is connected to the part of the coating located in the critical area (15) of the jet nozzle (12) by means of a surface having a curved profile (20).

Abstract: According to the invention, means (11) are provided that are able to recover, when said aircraft is in cruising flight phase or in a flight phase close to cruising, the energy of the release of the conditioned air when the latter passes from the conditioned zone (2) to outside the aircraft and to use the recovered energy in the air conditioning of the aircraft.

Abstract: An air inlet is of a scarf type and the internal profile of the upper sections of its lip includes, with respect to the identical and symmetrical horizontal sections of the lip, an internal bulge that is bigger for a larger scarf angle and that is a maximum at the upper vertical section.

Abstract: The air inlet is of scarf type and the internal profile [5S(&thgr;)] of the upper sections [S(&thgr;)] of its lip 1 comprises, with respect to the identical and symmetrical horizontal sections (Sb) of the said lip, an internal bulge (10) which is all the bigger the larger the scarf angle and which is a maximum at the upper vertical section [S(0)].