A propulsion system coupled to a vehicle. The system includes a diffusing structure and a conduit portion configured to introduce to the diffusing structure through a passage a primary fluid produced by the vehicle. The passage is defined by a wall, and the diffusing structure comprises a terminal end configured to provide egress from the system for the introduced primary fluid. A constricting element is disposed adjacent the wall. An actuating apparatus is coupled to the constricting element and is configured to urge the constricting element toward the wall, thereby reducing the cross-sectional area of the passage.

A propulsion system coupled to a vehicle. The system includes a diffusing structure and a conduit portion configured to introduce to the diffusing structure through a passage a primary fluid produced by the vehicle. The passage is defined by a wall, and the diffusing structure comprises a terminal end configured to provide egress from the system for the introduced primary fluid. A constricting element is disposed adjacent the wall. An actuating apparatus is coupled to the constricting element and is configured to urge the constricting element toward the wall, thereby reducing the cross-sectional area of the passage.

A mixing tube with multiple shapes is provided, allowing additional injection of gas in order to keep the flow detached from the second shape in an ascent phase and to bring about, in a descent phase, a controlled detachment as a result of the change of slope between the two shapes. A propulsion nozzle for an engine of a spacecraft or aircraft is provided including such a mixing tube and a method for controlling the speed transition of the propulsion gases in such a nozzle in accordance with the altitude. Also, a method is provided for vectorising the thrust in such a nozzle by radial and asymmetrical injection of gas and a control method which prevents re-attachment of the jet to the second shape of such a propulsion nozzle for an engine of a spacecraft when it is in the take-off or landing phase.

A mixing tube with multiple shapes is provided, allowing additional injection of gas in order to keep the flow detached from the second shape in an ascent phase and to bring about, in a descent phase, a controlled detachment as a result of the change of slope between the two shapes. A propulsion nozzle for an engine of a spacecraft or aircraft is provided including such a mixing tube and a method for controlling the speed transition of the propulsion gases in such a nozzle in accordance with the altitude. Also, a method is provided for vectorising the thrust in such a nozzle by radial and asymmetrical injection of gas and a control method which prevents re-attachment of the jet to the second shape of such a propulsion nozzle for an engine of a spacecraft when it is in the take-off or landing phase.

An apparatus is provided for an aircraft propulsion system. This apparatus includes an exhaust nozzle. The exhaust nozzle includes a flowpath, a passage, an outer door, an inner door and an actuator configured to move the outer door and the inner door between an open arrangement and a closed arrangement. The flowpath extends axially along a centerline through the exhaust nozzle. The passage extends laterally into the exhaust nozzle to the flowpath when the outer door and the inner door are in the open arrangement. The outer door is configured to pivot inwards towards the centerline when the outer door moves from the closed arrangement to the open arrangement. The inner door is configured to pivot outwards away from the centerline when the inner door moves from the closed arrangement to the open arrangement.

The invention relates to an exhaust case (15) for a turbomachine extending along a longitudinal axis (X), comprising: an annular shroud (23) having a wall (24) extending along the longitudinal axis (X) from a first flange (25), a plurality of openings (27) being provided through the wall (24); a plurality of mouths (28) each forming a channel (29) extending upstream to downstream between a respective inlet (30) and one of the openings (27), each mouth (28) having: a docking flange (31) at the inlet (30) having a radially inner edge (32) which is in contact with the first flange (25) of the annular shroud (23), a mouth wall (34) delimiting the channel (29) and comprising a radially inner wall portion (35) which is formed by a thickened section made on the wall (24) of the shroud (23).

The invention relates to an exhaust case (15) for a turbomachine extending along a longitudinal axis (X), comprising: an annular shroud (23) having a wall (24) extending along the longitudinal axis (X) from a first flange (25), a plurality of openings (27) being provided through the wall (24); a plurality of mouths (28) each forming a channel (29) extending upstream to downstream between a respective inlet (30) and one of the openings (27), each mouth (28) having: a docking flange (31) at the inlet (30) having a radially inner edge (32) which is in contact with the first flange (25) of the annular shroud (23), a mouth wall (34) delimiting the channel (29) and comprising a radially inner wall portion (35) which is formed by a thickened section made on the wall (24) of the shroud (23).

A jet noise suppressor including a nozzle having a front end and an opposed rear end, spokes extending radially inward from the nozzle, the spokes defining vents, and a center-body connected to the spokes and in fluid communication with the vents, the center-body being positioned centrally within the nozzle and including a closed front end and an open rear end, wherein the front end of the nozzle entrains a first ambient airflow passing through the nozzle and exiting the rear end of the nozzle proximate a periphery of the nozzle, and wherein the vents entrain a second ambient airflow passing through the center-body and exiting the rear end of the nozzle proximate a center of the nozzle.

A propulsion system coupled to a vehicle. The system includes a diffusing structure and a conduit portion configured to introduce to the diffusing structure through a passage a primary fluid produced by the vehicle. The passage is defined by a wall, and the diffusing structure comprises a terminal end configured to provide egress from the system for the introduced primary fluid. A constricting element is disposed adjacent the wall. An actuating apparatus is coupled to the constricting element and is configured to urge the constricting element toward the wall, thereby reducing the cross-sectional area of the passage.

A propulsion system coupled to a vehicle. The system includes a diffusing structure and a conduit portion configured to introduce to the diffusing structure through a passage a primary fluid produced by the vehicle. The passage is defined by a wall, and the diffusing structure comprises a terminal end configured to provide egress from the system for the introduced primary fluid. A constricting element is disposed adjacent the wall. An actuating apparatus is coupled to the constricting element and is configured to urge the constricting element toward the wall, thereby reducing the cross-sectional area of the passage.