Patent ID: 7967105
Filing Date: 2011-06-28
Classification: B64D,F02C

Abstract:
1. An inlet for an aviation engine, comprising: a lip surface of the inlet; an interior surface of the inlet extending inward from the lip surface inside the inlet; a first acoustic lining segment positioned downstream from the lip surface and a second acoustic lining segment positioned downstream from the first acoustic lining segment, each of the first and second lining segments having an exposed surface defining a portion of the interior surface of the inlet; a first annular blowing slot positioned immediately upstream from the first acoustic lining segment, extending circumferentially around the interior surface and configured to blow a first flow of air along the interior surface of the inlet such that the first flow of air flows over the first and second acoustic lining segments; and a third acoustic lining segment positioned downstream from the second acoustic lining segment and having an exposed surface defining a portion of the interior surface of the inlet; and a second annular blowing slot positioned immediately upstream from the third acoustic lining segment and configured to blow a second flow of air along the interior surface of the inlet such that the second flow of air flows over the third acoustic lining segment; each of the first, second, and third acoustic lining segments being optimized for a respective noise frequency that is different from the each of the other acoustic lining segments.