Abstract: An aircraft includes a first outer surface exposed to a hot air flow flowing in a flow direction and a device for generating a film of cold air in contact with a region to be protected of the first outer surface. The device includes a cold air outlet arranged upstream of the region to be protected as seen in the flow direction, and an inlet arranged at a second outer surface of the aircraft in contact with cold air. The inlet is arranged such that a pressure gradient exists between the inlet and the outlet so as to generate a natural flow of cold air from the inlet to the outlet as well as means to cause said inlet to communicate with said outlet.

Abstract: An air ejection device comprises an aerodynamic profile provided with a slot and an ejection nozzle. The device comprises a flexible tongue fixed flush with the aerodynamic profile in such a way as to obstruct the slot, the tongue being able to lift under the effect of a pressure differential between the air situated in the ejection nozzle and the outside air. The tongue makes it possible for the slot made in the profile to be obstructed during phases of flight during which the ejection of the air is unnecessary, and prevents external air from entering the slot. The flow of air over the aerodynamic profile is unaffected, and there is no increase in drag. Because the tongue lifts as a result of a pressure differential, it does not require any control mechanism to lift it.

Abstract: A turbomachine assembly comprising a device that attenuates noise by ejecting jets of fluid, this device comprising fluid supply ducts, fluid ejection tubes and a distribution duct of annular shape. The distribution duct is connected firstly to inlets of the ejection tubes and secondly to outlets of the fluid supply ducts so as to create a flow path for the circulation of fluid from the inlets of the fluid supply ducts to the outlets of the ejection tubes.

Abstract: An air ejection device comprises an aerodynamic profile provided with a slot and an ejection nozzle. The device comprises a flexible tongue fixed flush with the aerodynamic profile in such a way as to obstruct the slot, the tongue being able to lift under the effect of a pressure differential between the air situated in the ejection nozzle and the outside air. The tongue makes it possible for the slot made in the profile to be obstructed during phases of flight during which the ejection of the air is unnecessary, and prevents external air from entering the slot. The flow of air over the aerodynamic profile is unaffected, and there is no increase in drag. Because the tongue lifts as a result of a pressure differential, it does not require any control mechanism to lift it.

Abstract: An acoustic treatment panel includes an acoustically resistive layer that defines a surface of an aircraft that is in contact with an aerodynamic stream, a reflective layer (50) between which are arranged at least one alveolar structure (52) with a number of cells dedicated to the acoustic treatment, and de-icing cavities (58) in which hot air circulates in contact with the acoustically resistive layer to ensure a frost treatment, characterized in that it includes holes for supplying de-icing cavities (58) with hot air and in that the capacity to treat the frost is adjusted along the zones by modifying the open surface ratio that results from the holes.

Abstract: An air inlet of an aircraft nacelle includes a pipe, extending over the circumference of the air inlet and defined in the back by a front frame, and an element for the localized injection of hot air into the pipe, thus ensuring the flow of hot air into the pipe in one direction along the circumference of the nacelle. The inlet includes at least one vortex generator (38) in the pipe (22), the generator being plate-shaped or shaped in a manner projecting from the wall of the pipe (22), in order to disrupt the hot air flow so as to compensate the effect of the centrifugal force and reduce the temperature gradient between the inside and outside of the pipe (22).

Abstract: An aircraft nacelle air intake includes a duct extending around the circumference of the air intake and elements (24) for the localized injection of hot air into the duct to make the hot air circulate in the duct along its circumference, characterized in that the injection elements (24) include a collector tank in a plane secant with the direction of the stream of air flowing through the duct including at least one hole (44) allowing the air stream flowing in the duct to pass through it and a plurality of injection orifices (46) which are connected to a hot air supply and arranged around the passage hole or around and/or between the passage holes (44).

Abstract: An aircraft includes a first outer surface exposed to a hot air flow flowing in a flow direction and a device for generating a film of cold air in contact with a region to be protected of the first outer surface. The device includes a cold air outlet arranged upstream of the region to be protected as seen in the flow direction, and an inlet arranged at a second outer surface of the aircraft in contact with cold air. The inlet is arranged such that a pressure gradient exists between the inlet and the outlet so as to generate a natural flow of cold air from the inlet to the outlet as well as means to cause said inlet to communicate with said outlet.

Abstract: An aircraft nacelle includes a pipe, a peripheral wall, a lip connecting the pipe and peripheral wall and delimiting an air intake. A frost treatment system treats a zone extending along a longitudinal section of a point A at the peripheral wall at a point B at the pipe and includes a front frame delimiting with the lip a pipe circulating de-icing hot air. An acoustic pipe coating includes a reflective layer, at least one alveolar structure, and at least one acoustically resistive structure. The front frame includes a junction zone with the lip and/or the pipe offset toward the nacelle front relative to B. Pipes inside the lip and the pipe convey hot air from the pipe to circularly arranged discharges corresponding to B. The pipes extend beyond the junction between the front frame and the lip and/or the pipe and are delimited by at least one isolating partition.

Abstract: The invention relates to an aircraft nacelle that comprises a discharge means (50) for establishing a communication between the inside of the nacelle and the outside thereof, and a junction area between two members (54, 56), and at which the two members are superimposed, both members each having a surface defining the outer surface of the nacelle on either side of the junction area, characterized in that said discharge means (50) includes a dual-portion shim (52), i.e. a first portion provided between the superimposed panels and including at least one protruding and/or recessed member for forming a passage between said panels in order to establish a communication between the inside and the outside of the nacelle, and a second portion at the level of only one panel, i.e. that located inside at the junction area, in order to protect the same against excessive temperatures.

Abstract: An aircraft nacelle air intake includes a duct extending around the circumference of the air intake and elements (24) for the localized injection of hot air into the duct to make the hot air circulate in the duct along its circumference, characterized in that the injection elements (24) include a collector tank in a plane secant with the direction of the stream of air flowing through the duct including at least one hole (44) allowing the air stream flowing in the duct to pass through it and a plurality of injection orifices (46) which are connected to a hot air supply and arranged around the passage hole or around and/or between the passage holes (44).

Abstract: An air inlet of an aircraft nacelle includes a pipe, extending over the circumference of the air inlet and defined in the back by a front frame, and an element for the localized injection of hot air into the pipe, thus ensuring the flow of hot air into the pipe in one direction along the circumference of the nacelle. The inlet includes at least one vortex generator (38) in the pipe (22), the generator being plate-shaped or shaped in a manner projecting from the wall of the pipe (22), in order to disrupt the hot air flow so as to compensate the effect of the centrifugal force and reduce the temperature gradient between the inside and outside of the pipe (22).

Abstract: Disclosed is a method for improving the performance of transport aircraft. In particular, the aircraft is provided with a rounded nose cone in front of a center of gravity of the aircraft. The rounded nose cone has an upper longitudinal surface and a lower longitudinal surface configured, respectively, to generate a lifting force and a negative lifting force and produce a resultant that is lifting and to produce an auxiliary nose-up moment. The method involves shaping the nose cone to increase the lifting resultant. This shaping is carried out-by increasing the upper longitudinal surface of the nose cone, so as to increase the lifting force, and by reducing the lower longitudinal surface of the nose cone, so as to decrease the negative lifting force.

Abstract: An air discharge device includes a grid that is connected to an aerodynamic surface of an aircraft. The grid includes a number of openings delimited by intermediate zones that are arranged in the extension of the aerodynamic surface of the aircraft and at least one longitudinal reinforcement separating the openings into at least two stages. The dimensions and/or the surface ratio of the perforated zones that correspond to openings and non-perforated zones that correspond to intermediate zones or to the longitudinal reinforcement are such that they create a depression close to the air discharge.

Abstract: A vortex-generating device is presented to reduce a thermal exposure of an aircraft to hot exhaust gases discharged from an aircraft engine. The engine also discharges cold air from a fan of the engine. The aircraft engine may be coupled to the aircraft via a support mast located on a main wing. A portion of the support mast of an aircraft engine is located near a hot gas flow being discharged from the engine. The vortex-generating device is positioned on a surface of the support mast. The device generates a vortex which crosses the hot gases and prevents the hot gas flow from reaching a heat sensitive portion of the support mast. This device is adaptable to the operating conditions of an already-built aircraft without any notable increased weight.

Abstract: An acoustic treatment panel includes an acoustically resistive layer that defines a surface of an aircraft that is in contact with an aerodynamic stream, a reflective layer (50) between which are arranged at least one alveolar structure (52) with a number of cells dedicated to the acoustic treatment, and de-icing cavities (58) in which hot air circulates in contact with the acoustically resistive layer to ensure a frost treatment, characterized in that it includes holes for supplying de-icing cavities (58) with hot air and in that the capacity to treat the frost is adjusted along the zones by modifying the open surface ratio that results from the holes.

Abstract: The invention relates to an aircraft nacelle that comprises a discharge means (50) for establishing a communication between the inside of the nacelle and the outside thereof, and a junction area between two members (54, 56), and at which the two members are superimposed, both members each having a surface defining the outer surface of the nacelle on either side of the junction area, characterised in that said discharge means (50) includes a dual-portion shim (52), i.e. a first portion provided between the superimposed panels and including at least one protruding and/or recessed member for forming a passage between said panels in order to establish a communication between the inside and the outside of the nacelle, and a second portion at the level of only one panel, i.e. that located inside at the junction area, in order to protect the same against excessive temperatures.

Abstract: An aircraft nacelle includes a pipe, a peripheral wall, a lip connecting the pipe and peripheral wall and delimiting an air intake. A frost treatment system treats a zone extending along a longitudinal section of a point A at the peripheral wall at a point B at the pipe and includes a front frame delimiting with the lip a pipe circulating deicing hot air. An acoustic pipe coating includes a reflective layer, at least one alveolar structure, and at least one acoustically resistive structure. The front frame includes a junction zone with the lip and/or the pipe offset toward the nacelle front relative to B. Pipes inside the lip and the pipe convey hot air from the pipe to circularly arranged discharges corresponding to B. The pipes extend beyond the junction between the front frame and the lip and/or the pipe and are delimited by at least one isolating partition.

Abstract: According to the invention, the nose cone (2.I) of the aircraft is modified so as to increase the lifting resultant (R?).

Abstract: An air discharge device in the form of a grid that is connected to an aerodynamic surface of an aircraft, whereby includes a number of openings delimited by intermediate zones that are arranged in the extension of the aerodynamic surface of the aircraft and at least one longitudinal reinforcement or passage separating the openings into at least two stages, where the arrangement, the dimensions and/or the surface ratio of the perforated zones that correspond to openings and non-perforated zones that correspond to intermediate zones or to the passage(s) are such that they make possible creating a depression close to the air discharge.