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; and a divider positioned in the inlet, the divider being located to separate a first portion of the inlet from a second portion of the inlet, the first portion being configured to co

We claim: 1. An inlet system for an aircraft auxiliary power unit, comprising: an inlet having an entrance aperture; and a divider positioned in the inlet, the divider being located to separate a first portion of the inlet from a second portion of the inlet, the first portion being configured to couple to an engine air intake of an aircraft auxiliary power unit, the second portion being configured to direct air away from the air intake, the divider being 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 a second distortion level to the second portion of the inlet, with (a) the first total pressure level higher than the second total pressure level, and (b) the second distortion level higher than the first distortion level. 2. 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. 3. 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 portion of the inlet; and a compartment disposed around the auxiliary power unit, wherein the second portion of the inlet is positioned to direct air into the compartment. 4. 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 entrance aperture between an open position and a closed position. 5. 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 entrance aperture between an open position and a closed position, and wherein at least part of the inlet door sealably engages the divider when the inlet door is in the closed position. 6. The system of claim 1 wherein the divider is a first divider and wherein the system further comprises a second divider positioned to separate a third portion of the inlet from the first and second portions and direct a portion of the air away from the air intake. 7. The system of claim 1 wherein the inlet has an aperture edge, and wherein the divider is positioned at least approximately parallel to at least a portion of the aperture edge. 8. The system of claim 1 wherein the inlet has an aperture edge, and wherein the divider is oriented obliquely to the nearest portion of the aperture edge spaced apart from divider. 9. An inlet system for an aircraft auxiliary power unit, comprising: an aircraft fuselage portion; an inlet having an entrance aperture, the entrance aperture having a first surface portion positioned proximate to a surface of the aircraft fuselage portion, a second surface portion spaced apart from the first surface portion and located aft of the first surface portion, and third and fourth surface portions extending between the first and second surface portions; and a divider positioned in the inlet and generally aligned with the third surface portion, wherein the inlet includes a first flow channel between the divider and the fourth surface portion, and a second flow channel between the divider and the third surface portion, the first flow channel being configured to couple to an engine air intake of an aircraft auxiliary power unit, the second flow channel being configured to direct air away from the air intake, the first flow channel being positioned to direct air having a first total pressure level and a first distortion level, the second flow channel being positioned to direct air having a second total pressure level and a second distortion level, with (a) the first total pressure level higher than the second total pressure level, and (b) the second distortion level higher than the first distortion level. 10. The system of claim 9 wherein the inlet aperture has a generally rectangular shape. 11. The system of claim 9, 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 flow channel of the inlet is positioned to direct air into the compartment. 12. The system of claim 9, 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. 13. An inlet system for an aircraft auxiliary power unit, comprising: an aircraft fuselage portion; an inlet having an entrance aperture, the entrance aperture having a first surface portion positioned proximate to a surface of the aircraft fuselage portion, a second surface portion spaced apart from the first surface portion and located aft of the first surface portion, and third and fourth surface portions extending between the first and second surface portions; and a divider positioned in the inlet and generally aligned with the first surface portion, wherein the inlet includes a first flow channel between the divider and the second surface portion, and a second flow channel between the divider and the first surface portion, the first flow channel being configured to be coupled to an engine air intake of an aircraft auxiliary power unit, the second flow channel being configured to direct air away from the air intake, the first flow channel being positioned to direct air having a first total pressure level and a first distortion level, the second flow channel being positioned to direct air having a second total pressure level and a second distortion level, with: (a) the first total pressure level higher than the second total pressure level; or (b) the second distortion level higher than the first distortion level; or (c) both (a) and (b). 14. The system of claim 13 wherein the inlet aperture has a generally rectangular shape. 15. The system of claim 13 wherein the inlet includes an inlet duct elongated in a direction generally transverse to a plane of the entrance aperture. 16. The system of claim 13, 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 flow channel of the inlet is positioned to direct air into the compartment. 17. An inlet system for an aircraft auxiliary power unit, comprising: an inlet having an entrance aperture; and separation means for separating flow in the inlet into a first portion directed to an engine air intake of an aircraft auxiliary power unit and a second portion directed away from the air intake, the first portion having a first total pressure level and a first distortion level and the second portion having a second total pressure level and a second distortion level, with (a) the first total pressure level higher than the second total pressure level, and (b) the second distortion level higher than the first distortion level. 18. The system of claim 17 wherein the separation means includes a divider positioned in the inlet. 19. The system of claim 17 wherein the separation means includes a first divider and a second divider and wherein the first portion of the flow passes between the two dividers. 20. An aircraft, comprising: a fuselage; a wing; an auxiliary power unit compartment carried by at least one of the fuselage and the wing; an auxiliary power unit having an air intake and being housed in the auxiliary power unit compartment; an inlet having an entrance aperture; and a divider positioned in the inlet, the divider being located to separate a first portion of the inlet from a second portion of the inlet, the first portion being coupled to the air intake of aircraft auxiliary power unit, the second portion being positioned to direct air away from the air intake and into the auxiliary power unit compartment, the divider being 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 a second distortion level to the second portion of the inlet, with (a) the first total pressure level higher than the second total pressure level, and (b) the second distortion level higher than the first distortion level. 21. The aircraft of claim 20 wherein the entrance aperture of the inlet for the auxiliary power unit is positioned in an aft portion of the fuselage. 22. The system of claim 20 wherein the inlet aperture has a generally rectangular shape. 23. The system of claim 20 wherein the inlet includes an inlet duct elongated in a direction generally transverse to a plane of the entrance aperture. 24. The system of claim 20 wherein the divider includes a first divider and wherein the system further comprises a second divider, with the first portion of the inlet being positioned between the first and second dividers. 25. The system of claim 20, 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. 26. An aircraft, comprising: a fuselage; a wing; an auxiliary power unit compartment carried by at least one of the fuselage and the wing; an auxiliary power unit having an air intake and being housed in the auxiliary power unit compartment; an inlet having an entrance aperture, the entrance aperture having a first surface portion positioned to be proximate to a surface of the fuselage, a second surface portion spaced apart from and aft of 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; a second divider positioned in the inlet and generally aligned with the fourth surface portion, wherein the inlet 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 coupled to the engine, air intake of the aircraft auxiliary power unit, the second and third flow channels being directed into the auxiliary power unit compartment; and an inlet door positioned at least proximate to the entrance aperture of the inlet, the inlet door being movable relative to the inlet aperture between an open position and a closed position, and wherein at least part of the inlet door sealably engages the first and second dividers when the inlet door is in the closed position. 27. The aircraft of claim 26 wherein the entrance aperture of the inlet has a generally rectangular shape. 28. A method for providing flow to an aircraft auxiliary power unit, comprising: receiving flow in an inlet; providing a first portion of the flow having a first total pressure level and a first distortion level to an engine air intake of an auxiliary power unit; and directing a second portion of the flow having a second total pressure level and a second distortion level away from the engine air intake, wherein (a) the first total pressure level is higher than the second total pressure level, and (b) the second distortion level is higher than the first distortion level. 29. The method of claim 28 wherein directing a second portion of the flow includes directing a vortex flow away from the engine air intake. 30. The method of claim 28 wherein directing a second portion of the flow includes directing a vortex while the aircraft operates on the ground. 31. The method of claim 28 wherein directing a second portion of the flow includes directing a second portion of the flow while the aircraft is in flight. 32. The method of claim 28 wherein directing a second portion of the flow includes directing the second portion of the flow into a compartment housing the auxiliary power unit. 33. A method for providing flow to an aircraft auxiliary power unit, comprising: receiving a flow of air in an inlet 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; a second divider positioned in the inlet duct and generally aligned with the fourth surface portion; separating flow in a first flow channel between the first and second dividers from flow in a second flow channel between the first divider and the third surface portion, and from flow in a third flow channel between the second divider and the fourth surface portion; directing the flow in the first flow channel to an engine air intake of an aircraft auxiliary power unit; and directing the flows in the second and third flow channels to a compartment in which the auxiliary power unit is housed. 34. An inlet system for an aircraft auxiliary power unit, comprising: an inlet having an entrance aperture; and first and second dividers positioned in the inlet, the dividers being located to separate a first portion of the inlet from second and third portions of the inlet, the first portion being configured to couple to an engine air intake of an aircraft auxiliary power unit, the second and third portions being configured to direct air away from the air intake, the dividers being 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 a second distortion level to the second portion of the inlet, with (a) the first total pressure level higher than the second total pressure level, or (b) the second distortion level higher than the first distortion level, or both (a) and (b). 35. An inlet system for an aircraft auxiliary power unit, comprising: an inlet having an entrance aperture; and separation means for separating flow in the inlet into a first portion directed to an engine air intake of an aircraft auxiliary power unit and a second portion directed away from the air intake, wherein the separation means includes a first divider and a second divider and wherein the first portion of the flow passes between the two dividers, the first portion having a first total pressure level and a first distortion level and the second portion having a second total pressure level and a second distortion level, with (a) the first total pressure level higher than the second total pressure level, or (b) the second distortion level higher than the first distortion level, or both (a) and (b). 36. An aircraft, comprising: a fuselage; a wing; an auxiliary power unit compartment carried by at least one of the fuselage and the wing; an auxiliary power unit having an air intake and being housed in the auxiliary power unit compartment; an inlet having an entrance aperture; and first and second dividers positioned in the inlet to separate a first portion of the inlet from a second portion of the inlet, the first portion being positioned between the first and second dividers and being coupled to the air intake of aircraft auxiliary power unit, the second portion being positioned to direct air away from the air intake and into the auxiliary power unit compartment, the divider being 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 a second distortion level to the second portion of the inlet, with (a) the first total pressure level higher than the second total pressure level, or (b) the second distortion level higher than the first distortion level, or both (a) and (b).