Patent ID: 7344107

Claim:
An inlet system for an aircraft auxiliary power unit, comprising: an inlet having an entrance aperture, the entrance aperture having a first surface portion positioned to be proximate to an aircraft fuselage, a second surface portion spaced apart from the first surface portion, and third and fourth surface portions extending between the first and second surface portions; a first divider positioned in the inlet and generally aligned with the third surface portion; and a second divider positioned in the inlet duct and generally aligned with the fourth surface portion, wherein the inlet duct includes a first flow channel between the first and second dividers, a second flow channel between the first divider and the third surface portion, and a third flow channel between the second divider and the fourth surface portion, the first flow channel being configured to couple to an engine air intake of an aircraft auxiliary power unit, the second and third flow channels being configured to direct air away from the air intake.