Abstract: An aircraft including a fuselage extending along a longitudinal axis and having a rear end pointing reward of the aircraft, a main gear connected to the fuselage in a main gear position with respect to the longitudinal axis, and an engine for propelling the aircraft provided outside of the fuselage and attached to the fuselage via an attachment device between the main gear position and the rear end, wherein the engine generates a repulsive air stream streaming in the reverse direction. A surface element is moveably connected to the attachment device. The surface element moves between a neutral position at which it does not deflect the repulsive air stream, and a deflected position at which it deflects the repulsive air stream to assist aircraft rotation during take-off.

Abstract: Disclosed is an air intake arrangement for an aircraft. The arrangement includes an air intake orifice, which is configured to bleed off a flow of external air, pass the external air through at least one air passage channel and ventilate a confined zone of the aircraft. An aerodynamically controlled shut-off means, comprised of a controllable mobile element and control means, is configured to regulate flow of the external air through the air passage channel to vary a cross section of the air passage channel relative to aircraft speed. The control means are arranged in the air passage channel and include an aerodynamic surface configured to apply a lift force to the control means to vary the cross section of the air passage channel as the flow of external air passes through the channel and toward the confined zone.

Abstract: An aircraft including a fuselage extending along a longitudinal axis and having a rear end pointing reward of the aircraft, a main gear connected to the fuselage in a main gear position with respect to the longitudinal axis, and an engine for propelling the aircraft provided outside of the fuselage and attached to the fuselage via an attachment device between the main gear position and the rear end, wherein the engine generates a repulsive air stream streaming in the reverse direction. A surface element is moveably connected to the attachment device. The surface element moves between a neutral position at which it does not deflect the repulsive air stream, and a deflected position at which it deflects the repulsive air stream to assist aircraft rotation during take-off.

Abstract: A propeller for an aircraft turbine engine comprising a plurality of vanes as well as a hub having a plurality of accommodating ports receiving the bases of said vanes, each vane base being rotatably mounted in its associated accommodating port. The propeller also has at least one vane retaining ring structure in the radial direction outwardly from the hub, being cladded around the latter.

Abstract: Disclosed is a turbofan engine for an aircraft. An inner fan cowl of the turbofan engine bounds an annular cold-stream duct proximate to the engine's central hot-stream generator, and an outer fan cowl bounds the annular cold-stream duct proximate to an outer nacelle cowl. An annular boss is provided along the inner fan cowl, with the annular boss having a rounded cross section that projects with respect to a smooth shape configuration of the inner fan cowl. The annular boss is configured to locally change speed of a cold stream flow in the annular cold-stream duct from a subsonic range to a supersonic range and to originate a first shockwave characteristic in a succession of shockwave characteristics, with the first shockwave characteristic being inclined from its origin toward the rear portion of the turbofan engine.

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: Disclosed is a ventilating air intake arrangement of an aircraft. The arrangement includes at least one air duct connected to an air intake orifice. At least one confined zone connects with the air duct and the air intake orifice, and the confined zone is configured in a manner in which outside air enters through the air intake orifice. A controllable mobile element modifies the flow of air entering the confined zone by varying a cross section of the air duct. A control unit is used to control the controllable mobile element, with the control unit being arranged so as to control the controllable mobile element to vary the cross section of the at least one air duct as a function of speed and altitude of the aircraft.

Abstract: Disclosed is a method for producing a modified aircraft bypass turbojet engine having reduced sound output, in which the method is based on modifying an initial configuration of a rear portion of the turbojet engine to produce a modified rear portion of the turbojet engine. The modified rear portion includes a modified outer convex rear part shaped with a modified concave inner rear part that delimits an intermediate space beyond an initial cold stream outlet orifice. The intermediate space has a thickness at least equal to the thickness (E) of a sound deadening coating, which is placed in the intermediate space.

Abstract: An improved bypass turbojet engine includes a particularly shaped hot flow nozzle arranged about a particularly shaped type of boss. The boss is bulbous in shape and is connected by a first connecting surface to a turbine casing. The hot flow nozzle is formed as a single skin that extends in a rearward direction from an engine cowl, with the hot flow nozzle being connected to the engine cowl along a second connecting surface. The hot flow nozzle and the bulbous boss are positioned relative to one another to delimit a nominal nozzle throat section and a nominal outlet section for hot flow from a hot flow generator. The hot flow nozzle single skin is also approximately bulbous in shape and widens from the second connecting surface in a direction toward the engine cowl's external wall.

Abstract: A streamlined profile reducing the speed deficit in a wake, a pylon with such a profile, a propulsion assembly including such a pylon and an aircraft including this assembly. The profile has a device for suction of air from the boundary layer formed on this profile. This suctioned air is discharged with the aid of a nozzle the outlet of which is situated close to the trailing edge of the profile. Suction of the air and discharge thereof contribute to reducing the speed deficit downstream from the profile and therefore to reducing the turbulences in this zone.

Abstract: An aircraft engine assembly including a turboshaft engine with a propeller and an attachment pylon intended to be laterally attached on a rear portion of the structure of the aircraft is disclosed. The pylon has an outer surface forming an aerodynamic profile incorporating a trailing edge which is arranged upstream of the propeller of the turboshaft engine. The pylon includes a mobile rear flap at least partially defining the trailing edge and a controller which steers the incidence of the flap according to a law depending on the incidence of the aircraft.

Abstract: According to the invention, a plurality of embossments (20) having a rectangular section is provided at the inner periphery of the outlet opening (7) of the fan duct (12), said embossments being separated by longitudinal channels (21) having a convergent (22C) and a divergent (22D) for the cold flow (9).

Abstract: An aircraft ventilating air intake arrangement has an air passage channel and an air vent that ventilate a confined cone in an aircraft with fresh air entering the channel upstream and exiting the channel downstream towards the zone to be ventilated. A controllable blocking device enables the cross section of the channel to be varied with an elastically deformable membrane, under the action of fluid control, according to the speed and the altitude of the aircraft.

Abstract: An air intake arrangement includes a mobile plate controlled by at least one fluid communication passage or opening extending between the outer and inner surfaces of the mobile plate. The fluid communication passage or opening is located at least in the vicinity of a limited downstream area of the outer surface, is at a high pressure when the aircraft flies at cruising speed, and is capable of transmitting the high pressure to an extended area of the inner surface. The air flowing through the air intake arrangement may be used to refresh an enclosed area with electrical or mechanical equipment.

Abstract: The invention relates to a streamlined profile reducing the speed deficit in its wake, a pylon comprising such a profile, a propulsion assembly including such a pylon and an aircraft including this assembly. The profile comprises a device (40) for suction of air from the boundary layer formed on this profile. This suctioned air is discharged with the aid of a nozzle (48) the outlet of which is situated close to the trailing edge of the profile. Suction of the air and discharge thereof contribute to reducing the speed deficit downstream from the profile and therefore to reducing the turbulences in this zone.

Abstract: A pre-cooler having an annular cross-sectional shape about the axis of a pod and arranged inside the rear part of an inner shroud in external contact with a cold flow exiting a fan duct channel and in close contact with a cooling air stream drawn from the cold flow.

Abstract: According to the invention, a plurality of embossments (20) having a rectangular section is provided at the inner periphery of the outlet opening (7) of the fan duct (12), said embossments being separated by longitudinal channels (21) having a convergent (22C) and a divergent (22D) for the cold flow (9).

Abstract: A bypass turbine engine includes a precooler having an annular cross-sectional shape about the axis of a pod and arranged inside the rear part of an inner shroud in contact with a cold fluid exiting a fan duct.

Abstract: A propeller for an aircraft turbine engine comprising a plurality of vanes as well as a hub having a plurality of accommodating ports receiving the bases of said vanes, each vane base being rotatably mounted in its associated accommodating port. The propeller also has at least one vane retaining ring structure in the radial direction outwardly from the hub, being cladded around the latter.

Abstract: The invention relates to an arrangement (1) that comprises a mobile plate (18) controlled by a means for fluid communication (23) between the outer (18A) and inner surfaces of the mobile plate (18), wherein said means is located at least in the vicinity of a limited downstream area (24) of said outer surface (18A), are at a high pressure when the aircraft flies at cruising speed, and are capable of transmitting said high pressure to an extended area (26) of said inner surface.