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

A structural panel for an aircraft nacelle may comprise a core between a perforated skin and a septum. A plurality of dividing walls may extend between the septum and a backskin to define a plurality of cavities. Each cavity may be in fluid communication with a plurality of cells in the core through the septum. The cells and the cavities may attenuate noise.

A pylon is provided for connecting a propulsion system to an aircraft. The pylon includes a structure configured to structurally tie the propulsion system to the aircraft. The pylon also includes a pylon fairing configured to house and provide an aerodynamic cover for the structure. A lower aft fairing segment of the pylon fairing includes a plurality of apertures. The apertures are fluidly coupled with a sealed, sound attenuating chamber within the pylon.

Provided is a gas turbine system including: a compressor that compresses external air to generate compressed air; a combustor that burns the compressed air generated by the compressor together with fuel to generate a combustion gas; a turbine driven by the combustion gas generated by the combustor; an exhaust unit that guides a combustion gas that has passed through the turbine to outside; a nacelle formed in a cylindrical shape and extending along an axis line about which the turbine rotates and arranged so as to cover the compressor, the combustor, the turbine, and the exhaust unit; and an exit unit that guides the combustion gas, which passed through the turbine, to a discharge port provided in the surface of the nacelle.

An aircraft having a blended-wing-body configuration includes a centerbody, a pair of wings, at least one pair of engines, a pair of air inlets, and a pair of exhaust outlets. The centerbody has an airfoil-shaped cross section, an aircraft centerline, an aft portion, an upper mold line, a lower mold line, and a pair of centerbody leading edge portions respectively on opposite sides of the aircraft centerline. The wings are integral with the centerbody. The pair of engines are located on opposite sides of the aircraft centerline and are mounted within the centerbody between the upper mold line and the lower mold line. The pair of air inlets are located respectively along the centerbody leading edge portions and are respectively fluidly coupled to the pair of engines. The pair of exhaust outlets our located in the aft portion of the centerbody and our respectively fluidly coupled to the pair of engines.

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 cellular sound insulation structure and associated aircraft, a cell of which is provided with a diaphragm which includes a membrane having at least one orifice passing through a thickness of the membrane, and at least one tube surmounting the orifice and extending from a face of the membrane into one compartment of the cell, the tube comprising a free end, forming an acoustic outlet, which is positioned at a distance (p) from the base cross section of the cell. Also, a method for manufacturing such a cellular sound insulation structure, as well as to a tool for inserting a diaphragm into a cell. Such a cellular structure makes it possible to treat a wider acoustic frequency spectrum, and its acoustic dimensioning as well as its manufacture are simplified.

Systems and methods for noise suppression for aircraft are disclosed. The aircraft may include a fuselage. The aircraft may include a plurality of wings connected to or formed with the fuselage. The aircraft may include at least one engine configured to generate a propulsion force to propel the aircraft. The at least one engine may include a nozzle assembly having a nozzle body with an outlet that releases an exhaust air or a jet flow. The aircraft may include a noise suppression assembly. The noise suppression assembly may be configured to interact with the exhaust air or jet flow to substantially suppress, mitigate, reduce, or otherwise modify noise generated by the aircraft.

The present application relates to a sound insulating panel, suitable for use as a deflecting surface in jet blast deflectors.

Therefore, it is described a jet blast deflector fence, comprised of detachable sound insulating panels, forming a modular deflecting and noise absorbing surface, covering its entire frontal area that is aligned with the aircraft. This approach favours not only the maintenance procedures of the fence, but also allows noise absorption, in addition to redirecting the high energy exhausted from a jet engine.

Disclosed are laminates comprising a carbon fiber reinforced polymer sheet and a layer of polysilazane and methods for producing such laminates.