Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers. The polymeric material of the polymeric substrate may be structurally reinforced with materials that may include carbon, metal, or glass. The polymeric substrate may also include a plurality of layers to form a composite layup structure.

A sound attenuation device includes an acoustic panel having a first end and a second end spaced from the first end. The first end is configured for attachment to a first mount and the second end is configured for attachment to a second mount. The acoustic panel comprises a permeable skin and a septum, the septum having a length extending between the first end and the second end.

A jet noise suppressor and an airplane are provided. The jet noise suppressor includes a nozzle with a front end, a back end, an interior surface, and an exterior surface, a plurality of struts, and a plurality of vents. Each strut includes a base and a distal end with the base of each strut coupled to the interior surface of the nozzle, and each vent corresponds to a respective strut and is formed within the interior surface of the nozzle between the front end of the nozzle and the base of the respective strut.

[Object] To provide a supersonic aircraft and a method of reducing sonic booms, by which sonic booms due to engine exhaust can be reduced.

[Solving Means] A supersonic aircraft includes: a pair of engine nacelles 12R, 12L mounted on a fuselage 11 of an airframe 10; fins 13R, 13L as a pair of shielding plates that inhibits engine exhaust 15 discharged from jet engines (not shown) accommodated in the engine nacelles 12R, 12L from wrapping downward around the airframe 10; and a pair of horizontal tails 14R, 14L disposed behind the engine nacelles 12R, 12L. The fins 13R, 13L are disposed on the horizontal tails 14R, 14L so as to sandwich the engine exhaust 15, respectively.

An output cone of an aircraft propulsive assembly extending in a general direction called longitudinal direction and including a front part and a rear part. The longitudinal assembly of the front part and rear part forms an acoustic treatment system with at least two degrees of freedom. Such a system allows for the treatment of several frequency ranges or of one wide frequency range by the treatment of several overlapping ranges.

An airflow profiled structure having a profiled leading edge. The profiled leading edge having, along a leading edge line, a serrated profile line with a succession of teeth and depressions. The airflow profiled structure also includes a porous acoustically absorbent region located towards the bottom of the depressions.

An aircraft including a wing and an aeroengine having a longitudinal main axis and including a ducted nacelle with at least one fan is disclosed. The wing includes an acoustic treatment surface on a bottom portion of its outer shell on either side of the longitudinal main axis and over a width perpendicular to the longitudinal main axis that is not greater than three times the diameter of the fan. The acoustic treatment surface includes a layer of porous material for attenuating acoustic waves coming from the fan.

An airflow profiled structure having a profiled leading edge. The profiled leading edge having, along a leading edge line, a serrated profile line with a succession of teeth and depressions. The airflow profiled structure also includes a porous acoustically absorbent region located towards the bottom of the depressions.

A hybrid power tri-propeller helicopter apparatus for efficient and quiet flying includes a helicopter body, a cockpit portion, an engine portion, a tail boom portion, a gas motor, a generator, a battery pack, and an electric nose motor. A nose propeller and a lift propeller support are coupled to the helicopter body. A pair of electric lift motors is coupled to the lift propeller support and is in operational communication with the battery pack. A pair of lift propellers is coupled to the pair of lift motors. A tail fin and a pair of horizontal rear stabilizer fins are coupled to the tail boom portion. A pair of front stabilizer fins is coupled to the cockpit portion. A plurality of controls is coupled to the cockpit portion and is in operational communication with the nose motor, the pair of lift motors, and the pair of rear stabilizer fins.

The present disclosure particularly relates to an acoustic attenuation structure for a propulsion assembly of an aircraft. The acoustic attenuation structure includes an acoustically reflective wall and a sandwich panel. The sandwich panel includes a honeycomb structure surrounded by two acoustically porous skins, a rear skin and a skin. The acoustically reflective wall and the sandwich panel are arranged in such a way as to be separated by a layer of air.