APU exhaust system

Patent metadata

Field	Value
Publication number	US-9540114-B2
Application number	US-201414771431-A
Country	US
Kind code	B2
Filing date	Mar 3, 2014
Priority date	Mar 15, 2013
Publication date	Jan 10, 2017
Grant date	Jan 10, 2017

Abstract

An exhaust system for an APU in a gas turbine engine aircraft having a tail cone in which exhaust noise is reduced. An APU exhaust liner is attached to the APU and extending to an oval cutout at the tail cone The liner has a first constant cross section from the APU to a point proximate the tail cone, and a second, increasing cross section from the point proximate the tail cone to the liner cutout. The liner is turned toward the side of the tail. The liner cutout is further enlarged with at least one larger cutout.

First claim

The invention claimed is:

1. An exhaust system for an auxiliary power unit (APU) in tail cone section of an aircraft, the exhaust system comprising:
an exhaust outlet on a side of the tail cone section;
an APU exhaust liner attached to the APU and extending rearward from the APU to the exhaust outlet, the liner having a first section with a constant cross section from the APU to a point proximate the tail cone; and the liner having a second, larger diameter continuously increasing cross section from the downstream end of the first section to the outlet.

2. The exhaust system of claim 1 , wherein the liner is turned toward a side of the tail at the tail cone.

3. The exhaust system of claim 1 , where in the first diameter is about 27.8 cm (10.95 inches) and the second diameter is about 33.0 cm (13 inches).

4. The exhaust system of claim 1 , wherein the exhaust outlet is oval in shape.

5. The exhaust system of claim 4 , wherein the exhaust outlet is further enlarged with a second oval cutout of larger shape.

6. The exhaust system of claim 5 , wherein the exhaust outlet is still further enlarged with a third oval cutout of still larger shape.

7. A method for reducing the exhaust noise in an auxiliary power unit (APU) in a gas turbine engine aircraft having a tail cone, the method comprising:
receiving exhaust gas at a liner inlet adjacent the APU;
directing the exhaust gas through the liner from the liner inlet to an outlet in a side surface of a fuselage tail section; and
reducing the velocity of the exhaust gas in the liner before it exits the outlet in a region of the liner proximate the outlet by expanding the cross section of the liner and turning the enlarged liner to meet the outlet in a side surface of a fuselage tail section.

8. The method of claim 7 , wherein the liner is turned toward the side of the tail at the tail cone.

9. The method of claim 7 , where in the first diameter is about 27.8 cm (10.95 inches) and the second diameter is about 33.0 cm (13 inches).

10. The method of claim 7 , wherein the liner outlet is oval in shape.

11. The method of claim 10 , wherein the liner outlet is further enlarged with a second oval cutout of larger shape.

12. The method of claim 11 , wherein the liner outlet is still further enlarged with a third oval cutout of still larger shape.

13. An exhaust liner for an APU in a gas turbine engine aircraft having a tail cone ending with an outlet for discharging exhaust, the liner comprising:
a first section in the liner with a constant cross section from the APU to a point proximate the tail cone; and
a second, larger diameter in the liner with a continuously increasing cross section from the downstream end of the first section to the outlet of the liner at the tail cone.

14. The exhaust liner of claim 13 , wherein the exhaust liner is turned toward the side of the tail at the tail cone.

15. The exhaust liner of claim 13 , where in the first diameter is about 27.8 cm (10.95 inches) and the second diameter is about 33.0 cm (13 inches).

16. The exhaust liner of claim 13 , wherein the exhaust liner outlet is oval in shape.

17. The exhaust liner of claim 16 , wherein the exhaust liner outlet is further enlarged with a second oval cutout of larger shape.

18. The exhaust liner of claim 7 , wherein the exhaust liner outlet is still further enlarged with a third oval cutout of still larger shape.

Assignees

• United Technologies Corp

Inventors

• Nager Eric Andrew
• Napier James C
• Rehman Farooq
• Jones Anthony C

Classifications

• F05D2260/96

  Preventing, counteracting or reducing vibration or noise · CPC title

• B64D33/06 Primary

  Silencing exhaust or propulsion jets · CPC title

• F05D2220/50

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

• F02C7/32

  Arrangement, mounting, or driving, of auxiliaries · CPC title

• B64D2041/002

  Mounting arrangements for auxiliary power units (APU's) · CPC title