Abstract: An aircraft jet engine comprising a nozzle to eject a gas stream, and a system for reducing the noise generated by the ejection of the gas stream. This system comprises several ducts which each are connected upstream to a recess divided into several chambers and open, downstream, at the outlet of nozzle. In this way, each duct ejects a fluid jet deriving from the recess and which interacts with the gas stream of the engine. The system also comprises a pulsation means for the fluid jet which brings about its ejection at the nozzle outlet and/or modulates its speed by varying the volume contained in the recess.

Abstract: The invention relates to a method and device for controlling the mass flow rate of a sonic gas stream in a pipe. To carry out the above operation, an electric discharge is applied inside the pipe so as to create a plasma in the pipe. The electric discharge allows for an increase in the temperature of the gas stream and thus a variation in the mass flow rate or the pressure of the gas stream. By periodically emitting the electric discharge, a pulsed or adjustable gas jet is obtained at the outlet of the device. The gas jet can then be used to control a main stream.

Abstract: An aircraft jet engine with a longitudinal axis, including a wall enclosing a gas flow ejected from a downstream end of the wall in the longitudinal axis, plural ducts being distributed around the periphery of the downstream end of the wall each including a terminal section, including an outlet opening. Each duct can eject a fluid jet through the outlet opening thereof. The ducts are configured to eject the fluid jets essentially parallel to each other, each fluid jet ejected through the corresponding outlet opening forming a lateral angle with the longitudinal axis in a projection view in a plane with the longitudinal axis.

Abstract: An aircraft jet engine including a wall centered about a longitudinal axis and surrounding a stream of gas ejected at a downstream end of the wall in the direction of the axis, primary ducts distributed at the periphery of the downstream end of the wall configured on command each to eject a jet of primary fluid to interact with the ejected stream of gas, the primary ducts of each pair converging towards one another near the downstream end of the wall so that the primary jets ejected form two sides of a triangle that meet at the vertex thereof in a view projected onto a plane perpendicular to a transverse plane, and secondary ducts each associated with each pair of primary ducts and configured on command to eject a jet of secondary fluid directed into the triangle formed by the primary jets.

Abstract: The invention relates to a method and device for controlling the mass flow rate of a sonic gas stream in a pipe. To carry out the above operation, an electric discharge is applied inside the pipe so as to create a plasma in the pipe. The electric discharge allows for an increase in the temperature of the gas stream and thus a variation in the mass flow rate or the pressure of the gas stream. By periodically emitting the electric discharge, a pulsed or adjustable gas jet is obtained at the outlet of the device. The gas jet can then be used to control a main stream.

Abstract: The invention relates to an aircraft jet engine comprising a nozzle (2) intended to eject a gas stream, and a system for reducing the noise (3) generated by the ejection of the gas stream. This system comprises several ducts (11a) which each, on the one hand, are connected upstream to a recess divided into several chambers and, on the other hand, open, downstream, at the outlet of nozzle (2). In this way, each duct ejects a fluid jet deriving from the recess and which interacts with the gas stream of the engine. The system also comprises a pulsation means (12) for the fluid jet which brings about its ejection at the nozzle outlet and/or modulates its speed by varying the volume contained in the recess. The system is configured in particular for balancing static pressures between the chambers.

Abstract: A jet engine, including a wall surrounding a first gas flow ejected from a downstream end of the wall along a longitudinal axis, a second flow of gas running outside the wall in a direction of ejection of the first gas flow, at least one duct arranged on the periphery of the downstream end of the wall which is desired to eject a gas flow for interacting with one and/or the other gas flow, the at least one duct including a terminal section provided at the free end thereof with an outlet opening through which the fluid is ejected. The terminal section successively includes a first section of straight duct aligned along a median axis and a second duct section forming a bend relative to the straight section, the second portion having a free end provided with the outlet opening and sufficiently close to the median axis of the first section to give the terminal section a reduced restriction in a direction of formation of the bend.

Abstract: An aircraft engine having a longitudinal axis, including a wall surrounding a gas stream that is ejected at a downstream end of the wall along the longitudinal axis, wherein a plurality of conduits distributed at the periphery of the downstream end of the wall are each capable of ejecting, via an outlet orifice, a fluid jet in the form of a sheet, in such a way that the jets thus ejected each form a fluid perturbation around the ejected gas stream.

Abstract: A nozzle allowing the reduction of noise generated by aircraft jet engines having at least one output ring which disturbs the propulsion jet, and having at least one pair of conduits from which the propulsion of jet air is ejected at the output of the nozzle. The conduits of each pair are disposed convergent with respect to each other in order to generate a triangle of interaction of the air jets at the output ring.

Abstract: A jet engine, including a wall surrounding a first gas flow ejected from a downstream end of the wall along a longitudinal axis, a second flow of gas running outside the wall in a direction of ejection of the first gas flow, at least one duct arranged on the periphery of the downstream end of the wall which is desired to eject a gas flow for interacting with one and/or the other gas flow, the at least one duct including a terminal section provided at the free end thereof with an outlet opening through which the fluid is ejected. The terminal section successively includes a first section of straight duct aligned along a median axis and a second duct section forming a bend relative to the straight section, the second portion having a free end provided with the outlet opening and sufficiently close to the median axis of the first section to give the terminal section a reduced restriction in a direction of formation of the bend.

Abstract: An aircraft jet engine with a longitudinal axis, including a wall enclosing a gas flow ejected from a downstream end of the wall in the longitudinal axis, plural ducts being distributed around the periphery of the downstream end of the wall each including a terminal section, including an outlet opening. Each duct can eject a fluid jet through the outlet opening thereof. The ducts are configured to eject the fluid jets essentially parallel to each other, each fluid jet ejected through the corresponding outlet opening forming a lateral angle with the longitudinal axis in a projection view in a plane with the longitudinal axis.

Abstract: A nozzle allowing the reduction of noise generated by aircraft jet engines having at least one output ring which disturbs the propulsion jet, and having at least one pair of conduits from which the propulsion of jet air is ejected at the output of the nozzle. The conduits of each pair are disposed convergent with respect to each other in order to generate a triangle of interaction of the air jets at the output ring.

Abstract: The invention relates to an aircraft engine having a longitudinal axis (XX?), comprising a wall (30) surrounding a gas stream that is ejected at a downstream end (30a) of the wall along the longitudinal axis, characterized in that a plurality of conduits (60, 62, 64, 66, 68, 70, 72, 74) distributed at the periphery of the downstream end of the wall are each capable of ejecting, via an outlet orifice (60c), a fluid jet (76) in the form of a sheet, in such a way that the jets thus ejected each form a fluid perturbation around the ejected gas stream.

Abstract: A device for controlling propulsive gas mixing at an outlet of an aircraft jet engine, wherein propulsive jets are composed of a hot primary jet exiting from a nozzle of the jet engine and a secondary flux flowing between an external wall of the nozzle and an internal wall of the jet engine including a divergent trailing edge on the wall that generates conditions of a separation of the primary jet close to an existence limit value and a primary jet controller that enables control of passage of the primary jet from a separated state to a reattached state, and vice versa.

Abstract: A device for controlling propulsive gas mixing at an outlet of an aircraft jet engine, wherein propulsive jets are composed of a hot primary jet exiting from a nozzle of the jet engine and a secondary flux flowing between an external wall of the nozzle and an internal wall of the jet engine including a divergent trailing edge on the wall that generates conditions of a separation of the primary jet close to an existence limit value and a primary jet controller that enables control of passage of the primary jet from a separated state to a reattached state, and vice versa.