Abstract: A device for reducing the jet noise of a turbine engine includes an outer cover having an inside wall defining the outside of an annular passage for passing a bypass stream from the engine, the wall of the outer cover including a plurality of microjet circuits, each including intakes for taking a gas stream from the bypass stream flow passage and leading to a single feed duct, which in turn opens out into the trailing edge of the outer cover via at least one ejection grating suitable for splitting the intake gas stream into a plurality of gas streams of right sections of dimensions less than a right section of the feed duct.

Abstract: A device for reducing the jet noise of a turbine engine includes an outer cover having an inside wall defining the outside of an annular passage for passing a bypass stream from the engine, the wall of the outer cover including a plurality of microjet circuits, each including intakes for taking a gas stream from the bypass stream flow passage and leading to a single feed duct, which in turn opens out into the trailing edge of the outer cover via at least one ejection grating suitable for splitting the intake gas stream into a plurality of gas streams of right sections of dimensions less than a right section of the feed duct.

Abstract: The invention relates to a rear casing for a turbine engine comprising a primary body generating a primary flow (10) to be ejected through a primary nozzle (6), said rear casing (7) being shaped so as to be positioned downstream from the primary body and to define, on the inside of the turbine engine, the path followed by the primary flow downstream from the primary nozzle (6). The tail cone is characterised in that it comprises a connection to a system for supplying a pressurised gas and at least one perforation (8) for injecting the pressurised gas through the perforation and into the primary flow. The casing preferably comprises at least one means for rotating same about the axis of rotation of the mobile elements of the primary body.

Abstract: The invention concerns an afterbody for a mixed-flow turbojet engine having a central axis (LL), comprising a lobed mixer (6), having alternating hot lobes (12) projecting into the secondary flow (F2) and cold lobes (13) penetrating into the primary flow (F1), and a nozzle (1) comprising, on the trailing edge (14) of same, longitudinal indentations (15) defining a crown of noise-reducing chevrons (7), characterised in that, at a predefined abscissa (X5) on the central axis (LL) downstream from the lobed mixer (6), the inner wall (2) of the nozzle (1) has a neck where the surface area of the transverse passage section of a flow into the nozzle passes through a minimum, and in that, downstream from this predefined abscissa (X5), the radius of the inner wall (2) of the nozzle (1) varies between the indentations (15) and the chevrons (7) so as to produce, in the flow, in the vicinity of said crown of chevrons (7), azimuth fluctuations of the Mach number.

Abstract: The invention relates to a rear casing for a turbine engine comprising a primary body generating a primary flow (10) to be ejected through a primary nozzle (6), said rear casing (7) being shaped so as to be positioned downstream from the primary body and to define, on the inside of the turbine engine, the path followed by the primary flow downstream from the primary nozzle (6). The tail cone is characterised in that it comprises a connection to a system for supplying a pressurised gas and at least one perforation (8) for injecting the pressurised gas through the perforation and into the primary flow. The casing preferably comprises at least one means for rotating same about the axis of rotation of the mobile elements of the primary body.

Abstract: A mixer for a confluent-flow nozzle of a turbine engine is provided. The mixer includes: an annular cap designed to be centered on a longitudinal axis of the nozzle and having a stationary upstream portion and a downstream portion that is movable in rotation about the longitudinal axis relative to the stationary portion, the movable portion of the cap terminating at its downstream end in inner lobes alternating circumferentially with outer lobes; and a mechanism which imparts reciprocating rotary motion to the movable portion of the cap.

Abstract: The invention provides a mixer for a confluent-flow nozzle of a turbine engine, the mixer comprising an annular cap designed to be centered on a longitudinal axis of the nozzle and having a stationary upstream portion and a downstream portion that is movable in rotation about the longitudinal axis relative to the stationary portion, the movable portion of the cap terminating at its downstream end in inner lobes alternating circumferentially with outer lobes, and means for imparting reciprocating rotary motion to the movable portion of the cap.