Adaptive engine exhaust signature suppressor

Patent metadata

Field	Value
Publication number	US-10457409-B2
Application number	US-201615090013-A
Country	US
Kind code	B2
Filing date	Apr 4, 2016
Priority date	Apr 2, 2015
Publication date	Oct 29, 2019
Grant date	Oct 29, 2019

Abstract

An exhaust system has an engine exhaust plane associated with an entrance to the exhaust system, an exhaust exit plane associated with an exit of the exhaust system, a forward cap movable relative to the engine exhaust plane and configured to selectively intersect the engine exhaust plane, and an aft cap movable relative to the exhaust exit plane and configured to selectively intersect the exhaust exit plane.

First claim

What is claimed is:

1. An aircraft, comprising:
an exhaust system, comprising:
an engine exhaust plane associated with an entrance to the exhaust system;
an exhaust exit plane associated with an exit of the exhaust system;
a forward cap movable relative to the engine exhaust plane and configured to selectively intersect the engine exhaust plane;
an aft cap movable relative to the exhaust exit plane and configured to selectively intersect the exhaust exit plane:
a centerbody disposed at least partially longitudinally between the forward cap and the aft cap, each of the forward cap and the aft cap being movable relative to the centerbody, wherein the forward cap, the aft cap, and the centerbody collectively form an interior space configured to be fed cooling air via at least one duct connected with the centerbody, wherein a position of the centerbody is fixed relative to the at least one duct.

2. The aircraft of claim 1 , further comprising a motor, wherein the forward cap and the aft cap are moved in response to operation of the motor.

3. The aircraft of claim 2 ,
wherein the forward cap and the aft cap are configured to move at different rates.

4. The aircraft of claim 2 ,
wherein the forward cap and the aft cap are configured to move at the same rate.

5. The aircraft of claim 1 ,
wherein the forward cap comprises a first nose geometry and the aft cap comprises a second nose geometry, wherein the first nose geometry is the same as the second nose geometry.

6. The aircraft of claim 1 ,
wherein the forward cap comprises a first nose geometry and the aft cap comprises a second nose geometry, wherein the first nose geometry and the second nose geometry are different.

7. The aircraft of claim 1 , wherein a nose geometry of at least one of the forward cap and the aft cap comprises a conical shape.

8. The aircraft of claim 1 , further comprising a shaft, wherein the forward cap and the aft cap are both moved in response to rotation of the shaft.

9. The aircraft of claim 8 , wherein the shaft comprises threads having a first pitch associated with the forward cap and threads having a second pitch associated with the aft cap, wherein the first pitch and the second pitch are not equal.

10. An exhaust system, comprising:
an engine exhaust plane associated with an entrance to the exhaust system;
an exhaust exit plane associated with an exit of the exhaust system;
a forward cap movable relative to the engine exhaust plane and configured to selectively intersect the engine exhaust plane;
an aft cap movable relative to the exhaust exit plane and configured to selectively intersect the exhaust exit plane; and
a centerbody disposed at least partially longitudinally between the forward cap and the aft cap, each of the forward cap and the aft cap being movable relative to the centerbody, wherein the forward cap, the aft cap, and the centerbody collectively form an interior space configured to be fed cooling air via at least one duct connected with the centerbody, wherein a position of the centerbody is fixed relative to the at least one duct.

11. The aircraft of claim 10 , further comprising a motor, wherein the forward cap and the aft cap are moved in response to operation of the motor.

12. The aircraft of claim 11 , wherein the forward cap and the aft cap are configured to move at different rates.

13. The aircraft of claim 11 , wherein the forward cap and the aft cap are configured to move at the same rate.

14. The aircraft of claim 10 , wherein the forward cap comprises a first nose geometry and the aft cap comprises a second nose geometry, wherein the first nose geometry is the same as the second nose geometry.

15. The aircraft of claim 10 , wherein the forward cap comprises a first nose geometry and the aft cap comprises a second nose geometry, wherein the first nose geometry and the second nose geometry are different.

16. The aircraft of claim 10 , wherein a nose geometry of at least one of the forward cap and the aft cap comprises a conical shape.

17. The aircraft of claim 10 , further comprising a shaft, wherein the forward cap and the aft cap are both moved in response to rotation of the shaft.

18. The aircraft of claim 17 , wherein the shaft comprises threads having a first pitch associated with the forward cap and threads having a second pitch associated with the aft cap, wherein the first pitch and the second pitch are not equal.

19. A method of changing performance of an aircraft, comprising:
providing an exhaust system, comprising:
an engine exhaust plane associated with an entrance to the exhaust system;
an exhaust exit plane associated with an exit of the exhaust system;
a forward cap movable relative to the engine exhaust plane and configured to selectively intersect the engine exhaust plane;
an aft cap movable relative to the exhaust exit plane and configured to selectively intersect the exhaust exit plane; and
a centerbody disposed at least partially longitudinally between the forward cap and the aft cap, each of the forward cap and the aft cap being movable relative to the centerbody, wherein the forward cap, the aft cap, and the centerbody collectively form an interior space configured to be fed cooling air via at least one duct connected with the centerbody, wherein a position of the centerbody is fixed relative to the at least one duct; and
moving at least one of the forward cap and the aft cap through operation of a single movement production device.

20. The method of claim 19 , wherein the exhaust system further comprises a shaft, wherein the single movement production device comprises a single motor and wherein the forward cap and the aft cap are moved by the same shaft at different rates.

Assignees

• Bell Helicopter Textron Inc

Inventors

• Laramee Robert Michael
• Miller David L

Classifications

• B64D2033/045

  comprising infrared suppressors · CPC title

• B64D33/04 Primary

  of exhaust outlets or jet pipes · CPC title

• F05D2220/90

  in vehicles adapted for vertical or short take off and landing (v/stol vehicles) · CPC title

• F02K1/825 Primary

  Infrared radiation suppressors · CPC title