Patent ID: 6457676
Filing Date: 2002-10-01
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 defining a first porosity; a back surface offset from the inlet flow surface having second apertures defining a second porosity less than the first porosity, the second apertures being coupleable to a source of pressurized, heated gas and being sized to direct a quantity of the gas through the first apertures sufficient to at least restrict the formation of ice on the inlet flow surface; and an acoustic core positioned between the back surface and the inlet flow surface with at least a portion of the first apertures in fluid communication with the second apertures through the acoustic core.