초록 ▼

Dual flow auxiliary power unit (APU) inlets and associated systems and methods are disclosed. An inlet in accordance with one embodiment of the invention includes an entrance aperture and a divider positioned in the inlet and located to separate a first portion of the inlet from a second portion of

Dual flow auxiliary power unit (APU) inlets and associated systems and methods are disclosed. An inlet in accordance with one embodiment of the invention includes an entrance aperture and a divider positioned in the inlet and located to separate a first portion of the inlet from a second portion of the inlet. The first portion can be configured to couple to an engine air intake of an APU, and the second portion can be configured to direct air away from the air intake. The divider can be positioned to direct air having a first total pressure level and a first distortion level to the first portion of the inlet, and direct air having a second total pressure level and second distortion level to the second portion of the inlet. The first total pressure level can be approximately the same as or higher than the second total pressure level, or the second distortion level can be approximately the same as or higher than the first distortion level, or both.

대표청구항 ▼

We claim: 1. 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 thi

We claim: 1. 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. 2. The system of claim 1 wherein the first divider is generally parallel to the third surface portion and the second divider is generally parallel to the fourth surface portion. 3. The system of claim 1 wherein in the first divider extends outwardly and aft, and wherein the second divider extends outwardly and aft, away from the first divider. 4. The system of claim 1 wherein the inlet aperture has a generally rectangular shape. 5. The system of claim 1 wherein the inlet includes an inlet duct elongated in a direction generally transverse to a plane of the entrance aperture. 6. The system of claim 1, further comprising: the auxiliary power unit, and wherein the air intake of the auxiliary power unit is coupled to the first flow channel of the inlet; and a compartment disposed around the auxiliary power unit, wherein the second and third flow channels of the inlet are positioned to direct air into the compartment. 7. The system of claim 1, further comprising an inlet door positioned at least proximate to the entrance aperture of the inlet, the inlet door being movable relative to the aperture between an open position and a closed position.