Patent ID: 8234869

Claim:
An inlet for an aviation engine comprising: an exterior surface of the inlet extending a full length of the inlet and extending further downstream to form a nacelle cowling; a lip surface of the inlet; an interior surface of the inlet extending the full length of the inlet from the lip surface to a frontal interface of the aviation engine; a segment of a buzz saw lining immediately connected to the frontal interface of the aviation engine, and having an exposed surface defining a portion of the interior surface of the inlet; an annular tangential blowing slot positioned immediately upstream from the segment of the buzz saw lining and extending circumferentially 360 degrees around the interior surface of the inlet, blowing a flow of air at speeds greater than a mean speed of a flow of air of the inlet, with a source of the blowing air from a bleed of air flow of a fan of the aviation engine; Wherein in the segment of the buzz saw lining and the annular tangential blowing slot, whereby an improvement of attenuation of a buzz saw tone noise, comprising blowing the flow of air along a full length of a surface of the segment of the buzz saw lining, wherein the blowing of the flow of air at flow speeds greater than the mean speed of the flow of air of the inlet.