A gas turbine engine system according to an exemplary aspect of the present disclosure may include a fan nacelle that extends circumferentially about a fan, and at least one integrated mechanism coupled to the fan nacelle. The at least one integrated mechanism includes a variable fan nozzle and a thrust reverser, with the thrust reverser and the variable fan nozzle having a common part.

A gas turbine engine system according to an exemplary aspect of the present disclosure may include a fan nacelle that extends circumferentially about a fan, and at least one integrated mechanism coupled to the fan nacelle. The at least one integrated mechanism includes a variable fan nozzle and a thrust reverser, with the thrust reverser and the variable fan nozzle having a common part.

The present disclosure concerns a nacelle for an aircraft engine, which includes a thrust reverser cowling that is slidably mounted between a direct jet position, and a reversed jet position in which the cowling opens a passage in the nacelle and uncovers a deflection device, and at least one actuator for moving the cowling. The nozzle section of the cowling delimits at least one opening that is combined with a leakage door, the leakage door being movably mounted on the cowling between a closed position in which the door engages with the associated opening to counteract the flow of air through said opening, and an open escape position in which the door is retracted to allow a portion of the air flow to flow through said opening.

The present disclosure concerns a nacelle for an aircraft engine, which includes a thrust reverser cowling that is slidably mounted between a direct jet position, and a reversed jet position in which the cowling opens a passage in the nacelle and uncovers a deflection device, and at least one actuator for moving the cowling. The nozzle section of the cowling delimits at least one opening that is combined with a leakage door, the leakage door being movably mounted on the cowling between a closed position in which the door engages with the associated opening to counteract the flow of air through said opening, and an open escape position in which the door is retracted to allow a portion of the air flow to flow through said opening.

A nacelle exhaust nozzle having a deployable noise-reducing component is described. The noise-reducing component includes an annular perforated sleeve coinciding with the inner nacelle loft line and circumscribing a mixed exhaust gas flow exiting the nacelle. The annular perforated sleeve is radially spaced apart from of a displaceable wall of an inflatable envelope that is displaceable between a deployed position, wherein noise-reduction is active, and a retracted position, wherein noise-reduction is inactive. When the inflatable envelope is pressurized, portions of the displaceable wall project through openings in the perforated sleeve and into the exhaust gas flow to form a rough surface at the loft line which causes a reduction in noise level. The portions of the displaceable wall that project through the openings in the perforated sleeve when the inflatable enveloped is pressurized include a plurality of dimples formed on the inner wall and forming the rough surface.

An exhaust nozzle for a gas turbine engine according to an example of the present disclosure includes, among other things, a duct having a first surface and a second surface extending about a duct axis to define an exhaust flow path, and at least one effector positioned along the first surface. The at least one effector is pivotable about an effector axis to vary a throat area of the exhaust flow path. The at least one effector tapers along the effector axis. A method of exhaust control for a gas turbine engine is also disclosed.

An exhaust nozzle for a gas turbine engine according to an example of the present disclosure includes, among other things, a duct having a first surface and a second surface extending about a duct axis to define an exhaust flow path, and at least one effector positioned along the first surface. The at least one effector is pivotable about an effector axis to vary a throat area of the exhaust flow path. The at least one effector tapers along the effector axis. A method of exhaust control for a gas turbine engine is also disclosed.

Provided is a supersonic aircraft including: a shield that shields an engine exhaust flow discharged from a jet engine accommodated in an engine nacelle mounted on a fuselage of the aircraft to thereby reduce sonic booms due to the engine exhaust flow; and an exhaust nozzle that is provided in an exhaust port of the engine nacelle and that generates a sound source for high-frequency components at a position at which the shield is capable of shielding the high-frequency components of the engine exhaust flow, to thereby reduce jet noise having the high-frequency components, and promotes mixing of the engine exhaust flow that generates low-frequency noise components with an external air flow to thereby reduce jet noise having the low-frequency components.

Provided is a supersonic aircraft including: a shield that shields an engine exhaust flow discharged from a jet engine accommodated in an engine nacelle mounted on a fuselage of the aircraft to thereby reduce sonic booms due to the engine exhaust flow; and an exhaust nozzle that is provided in an exhaust port of the engine nacelle and that generates a sound source for high-frequency components at a position at which the shield is capable of shielding the high-frequency components of the engine exhaust flow, to thereby reduce jet noise having the high-frequency components, and promotes mixing of the engine exhaust flow that generates low-frequency noise components with an external air flow to thereby reduce jet noise having the low-frequency components.

An exhaust nozzle for a gas turbine engine according to an example of the present disclosure includes, among other things, a duct having a first surface and a second surface extending about a duct axis to define an exhaust flow path, and at least one effector positioned along the first surface. The at least one effector is pivotable about an effector axis to vary a throat area of the exhaust flow path. The at least one effector tapers along the effector axis. A method of exhaust control for a gas turbine engine is also disclosed.