Patent ID: 6371411
Filing Date: 2002-04-16
Classification: B64D,F01D,F02C,F05D

Abstract:
An ice protection system for an aircraft engine inlet, comprising:an external surface portion; an internal surface portion positioned inwardly of the external surface portion; a lip surface portion extending between the external surface portion and the internal surface portion to define a hilite, at least one of the lip surface portion and the internal surface portion defining an inlet flow surface having a minimum flow area aft of the hilite, the inlet flow surface having first apertures extending therethrough; a back surface offset from the inlet flow surface and having second apertures extending therethrough sized to pass a quantity of pressurized heated gas through the first apertures sufficient to at least restrict ice formation on the inlet flow surface, the second apertures positioned only in a region at or forward of the minimum flow area and coupleable to a source of the pressurized heated gas; and a sound-attenuating acoustic core positioned between the back surface and the inlet flow surface with the first apertures in fluid communication with the second apertures through the acoustic core.