Pressure influencing assembly for an aircraft auxiliary system

Patent metadata

Field	Value
Publication number	US-9254924-B2
Application number	US-201113208824-A
Country	US
Kind code	B2
Filing date	Aug 12, 2011
Priority date	Aug 12, 2011
Publication date	Feb 9, 2016
Grant date	Feb 9, 2016

Abstract

An exemplary pressure influencing assembly for an aircraft auxiliary system an inlet opening to an aircraft auxiliary system and an exhaust opening from the aircraft auxiliary system. Both the inlet opening and the exhaust opening face at least partially radially away from an axis. At least some of the inlet opening is circumferentially aligned with at least some of the exhaust opening relative to the axis.

First claim

We claim:

1. A pressure influencing assembly for an aircraft auxiliary system, comprising:
a compressor that provides compressed air for expansion across a turbine;
an inlet opening to the aircraft auxiliary system; and
an exhaust opening from the aircraft auxiliary system, wherein both the inlet opening and the exhaust opening face at least partially radially away from a rotational axis of the aircraft auxiliary system, both the inlet opening and the exhaust opening circumferentially spaced from an axially extending crown of a tail cone, wherein the aircraft auxiliary system is positioned within the tail cone, and the exhaust opening is positioned within a flowpath from the inlet opening, wherein the axially extending crown extends from a vertical stabilizer to an aftmost end of the tail cone, wherein the inlet opening and the exhaust opening are circumferentially misaligned about the rotational axis, and wherein at least some of the inlet opening is circumferentially overlapping with at least some of the exhaust opening relative to the rotational axis.

2. The pressure influencing assembly of claim 1 , including a door that selectively covers the inlet opening.

3. The pressure influencing assembly of claim 2 , wherein the door is hinged at an aft side of the inlet opening.

4. The pressure influencing assembly of claim 1 , wherein the rotational axis is aligned with a direction of flow through the aircraft auxiliary system.

5. The pressure influencing assembly of claim 1 , wherein the aircraft auxiliary system is received within a cavity established by an aircraft skin of the tail cone, and the inlet opening and the exhaust opening are located within an upper portion of the aircraft skin of the tail cone, wherein the aftmost end of the tail cone is located at a planar vertical boundary between the upper portion and a lower portion of the aircraft skin of the tail cone.

6. The pressure influencing assembly of claim 1 , wherein the inlet opening and the exhaust opening are configured to both face upwards relative to horizon when an aircraft having the aircraft auxiliary system has a neutral roll angle and is in straight and level flight.

7. The pressure influencing assembly of claim 1 , wherein the aircraft auxiliary system is a secondary engine of an aircraft.

8. The pressure influencing assembly of claim 1 , wherein the aircraft auxiliary system is received within a cavity established by an aircraft skin of the tail cone, and an outer surface of the aircraft skin is uninterrupted by any additional structure located on the outer surface between the inlet opening and the exhaust opening.

9. The pressure influencing assembly of claim 1 , wherein the aircraft auxiliary system is an aircraft auxiliary power unit.

10. A pressure influencing assembly for an aircraft auxiliary system comprising:
the aircraft auxiliary system arranged within a cavity established by an aircraft skin of a tail cone, the aircraft auxiliary system having a rotational axis and a compressor that provides a compressed air supply for expansion across a turbine;
an inlet duct that communicates an inlet flow radially through an inlet opening in the aircraft skin to the aircraft auxiliary system; and
an exhaust duct that communicates an exhaust flow radially through an exhaust opening in the aircraft skin away from the aircraft auxiliary system,
wherein the inlet opening and the exhaust opening are circumferentially misaligned about the rotational axis, and
wherein at least some of the inlet opening is circumferentially overlapping with at least some of the exhaust opening about the rotational axis,

the cavity terminates at an aft end, and the exhaust opening is axially spaced from the aft end.

11. The pressure influencing assembly of claim 10 , including a door that selectively restricts the inlet flow.

12. The pressure influencing assembly of claim 10 , wherein the aircraft skin terminates at an aft end, and the exhaust opening is axially spaced from the aft end.

13. The pressure influencing assembly of claim 10 , wherein the cavity terminates at an aft end, and the exhaust opening is axially spaced from the aft end.

14. The pressure influencing assembly of claim 10 , wherein the aircraft skin has an upper portion and a lower portion, and the inlet opening and the exhaust opening are both in the upper portion, wherein the tail cone has an aftmost end located at a planar vertical boundary between the upper portion and the lower portion.

15. The pressure influencing assembly of claim 10 , wherein the aircraft skin has an axially extending crown, and both the inlet opening and the exhaust opening are circumferentially spaced from the axially extending crown, wherein the axially extending crown extends from a vertical stabilizer to an aftmost end of the tail cone.

16. The pressure influencing assembly of claim 15 , wherein the aircraft auxiliary system is positioned within the cavity aft of the vertical stabilizer.

17. The pressure influencing assembly of claim 10 , wherein an outer surface of the aircraft skin is uninterrupted by any additional structure between the inlet opening and the exhaust opening.

18. A method of influencing pressure on an exhaust of an aircraft auxiliary system, comprising:
(a) exhausting a flow from the aircraft auxiliary system positioned within a tail cone of an aircraft, the aircraft auxiliary system including a compressor that provides a compressed air supply for expansion across a turbine; and
(b) disrupting the flow over an outer surface of the tail cone using an inlet opening, or both the inlet opening and an inlet door, to influence back pressure on an exhaust of the aircraft auxiliary system, the inlet opening and the exhaust both circumferentially offset from an axially extending crown of the aircraft auxiliary system, wherein the inlet opening is circumferentially misaligned from the exhaust about a rotational axis of the aircraft auxiliary system, wherein at least a portion of the exhaust and at least a portion of the inlet opening are circumferentially overlapping about the rotational axis, and wherein the axially extending crown extends from a vertical stabilizer to an aftmost end of the aircraft auxiliary system.

Assignees

• Nager Eric Andrew
• Jones Anthony C
• Hagshenas Behzad
• Thayalakhandan Nagamany
• Hamilton Sundstrand Corp

Inventors

• Nager Eric Andrew
• Jones Anthony C
• Hagshenas Behzad
• Thayalakhandan Nagamany

Classifications

• Y10T137/0536

  Highspeed fluid intake means [e.g., jet engine intake] · CPC title

• B64D2033/0213

  specially adapted for auxiliary power units (APU's) · CPC title

• B64D41/00 Primary

  Power installations for auxiliary purposes · CPC title