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Acoustic attenuation panel for ducted-fan turbine engine of aircraft, has porous material utilized as acoustic absorption material and attached to structuring skin, and stiffeners fixed on skin, where resistive layer is added on stiffeners
Acoustic attenuation panel for ducted-fan turbine engine of aircraft, has porous material utilized as acoustic absorption material and attached to structuring skin, and stiffeners fixed on skin, where resistive layer is added on stiffeners
The panel has a structuring skin (1), and a porous material (5) utilized as an acoustic absorption material and attached to the skin. The porous material is selected from foam, expanded material, felt or small sized element aggregate. The porous material is selected from metallic material, polymer material, ceramic material e.g. carbon foam, or composite material. Stiffeners are fixed on the skin, and a resistive layer is added on the stiffeners. The skin, the stiffeners and the layer are made of material e.g. metal alloy, ceramic, metal matrix composite and ceramic matrix composite. Independent claims are also included for the following: (1) an air intake structure for a turbojet engine nacelle of an aircraft, comprising a pneumatic de-icing compartment (2) a fixed internal structure for a turbojet engine nacelle of an aircraft, comprising an acoustic attenuation panel.
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