Patent ID: 9290274
Filing Date: 2016-03-22
CPC Classification: B64D,E04B,F02C,F05D,G10K

Claim Text:
1. An aircraft engine assembly comprising: an aircraft engine; a nacelle configured to surround the aircraft engine and having an inlet open to ambient air; an annular acoustic panel, comprising an open framework, made from a first material, forming a plurality of cells, and a surface treatment provided on the open framework to increase the sound attenuation of the open framework relative to the open framework without the surface treatment, the surface treatment comprising a surface modification including at least one of a nanostructure comprising filaments projecting away from the open framework, a coating, a particulate layer, a fabric, or a cellular solid body; wherein at least one of the length, angle of projection, and porosity of the filaments may be selected to attenuate one or more predetermined frequencies of sound, and the annular acoustic panel is provided within the nacelle and sound emitted from the aircraft engine is attenuated by the annular acoustic panel.