Method and apparatus for nozzle thrust vectoring

Patent metadata

Field	Value
Publication number	US-9551296-B2
Application number	US-201414158954-A
Country	US
Kind code	B2
Filing date	Jan 20, 2014
Priority date	Mar 18, 2010
Publication date	Jan 24, 2017
Grant date	Jan 24, 2017

Abstract

A thrust vectoring system is created with a convergent-divergent nozzle having a total angle no greater than 150 degrees. A divergent portion of the nozzle has a wall at a predetermined angle of at least 12° from the freestream direction. A disturbance generator is located on the wall to induce flow separation from the wall with the predetermined wall angle sufficient for the induced flow separation to extend upstream from disturbance generator substantially to a throat of the nozzle pressurizing the wall and creating a net vector angle in jet flow through the nozzle.

First claim

What is claimed is:

1. A thrust vectoring system comprising:
a convergent-divergent nozzle including:
a convergent inlet portion,
a divergent outlet portion having a divergent wall with a flatness defined, in a streamwise direction, by a curve having a second derivative with a magnitude of less than 0.005 inch −1 , and
a throat therebetween having a sharpness defined, in the streamwise direction, by a curve having a second derivative with a magnitude greater than 4 inch −1 ; and
a disturbance generator located in the divergent outlet portion at a location selected to induce shockless flow separation, wherein the divergent wall is a first wall and wherein the disturbance generator is located on a second wall adjacent to and substantially orthogonal to the first wall and configured to cause a separation pocket along the first wall, the orientation of the separation pocket extending from the throat to a downstream end of the nozzle and from a first lateral side of the first wall to a second lateral side of the first wall.

2. The thrust vectoring system of claim 1 , wherein the convergent inlet portion and the divergent outlet portion have a total angle no greater than 150 degrees and a divergence angle is at least 12 degrees relative to a streamwise nozzle axis and wherein the convergent inlet portion includes a convergent wall having a convergence angle greater than the divergence angle.

3. The thrust vectoring system of claim 2 , wherein the convergence angle is at least 18 degrees relative to the streamwise nozzle axis.

4. The thrust vectoring system of claim 1 , wherein the disturbance generator comprises an injection slot.

5. The thrust vectoring system of claim 1 , wherein the disturbance generator is a zero-net mass flux jet.

6. The thrust vectoring system of claim 1 , wherein the disturbance generator is located between 25% and 75% of a divergence length.

7. The thrust vectoring system of claim 1 , wherein the disturbance generator is a first disturbance generator, and wherein a second disturbance generator is located on the divergent wall and configured to cause a separation pocket along the divergent wall.

8. The thrust vectoring system of claim 7 , the divergent portion further comprising the second wall and a third wall adjacent to the first wall, the third wall including a third disturbance generator, the first disturbance generator positioned proximate an intersection of the first and second walls and the third disturbance generator position proximate an intersection of the first and third walls, said first and third disturbance generators cooperating with the second disturbance generator to induce flow separation on the first wall.

9. The thrust vectoring system of claim 8 , wherein the first and third disturbance generators are located downstream from the second disturbance generator.

10. The thrust vectoring system of claim 1 , wherein the disturbance generator includes an injection slot proximate an intersection of the first wall and the second wall.

11. The thrust vectoring system of claim 1 , wherein the disturbance generator comprises a first injection slot on the first wall of the nozzle and a second injection slot on the second wall of the nozzle.

12. The thrust vectoring system of claim 1 , wherein the disturbance generator is configured to provide a vectoring effectiveness of at least 8 for about 0.2% of injected flow.

13. The thrust vectoring system of claim 1 , wherein the convergent-divergent nozzle is a 3D nozzle and the disturbance generator comprises a plurality of injection slots arranged circumferentially around the divergent outlet portion of the nozzle.

14. The thrust vectoring system of claim 1 , wherein the throat has a sharpness defined, in a streamwise direction, by a curve having a second derivative with a magnitude of about 4 inch −1 to about 8 inch −1 .

15. The thrust vectoring system of claim 1 , wherein the divergent wall has a flatness defined, in a streamwise direction, by a curve having a second derivative with a magnitude of about 0.005 inch −1 to about 0.002 inch −1 .

16. A method for thrust vectoring comprising:
accelerating a flow to supersonic speed by passing a flow through a convergent-divergent nozzle, the convergent-divergent nozzle including a throat having a sharpness defined, in the streamwise direction, by a curve having a second derivative with a magnitude greater than 4 inch −1 , a total angle between convergent and divergent portions of the nozzle of less than 150°, and a divergence angle of the divergent portion of at least 12°, the convergent-divergent nozzle further including a disturbance generator located on the divergent portion; and
generating a disturbance by the disturbance generator to induce shockless flow separation from a first wall of the divergent portion, wherein the disturbance generator is located on a second wall adjacent to and substantially orthogonal to the first wall and configured to cause a separation pocket along the first wall, the orientation of the separation pocket extending from the throat to a downstream end of the nozzle and from a first lateral side of the first wall to a second lateral side of the first wall.

17. The method of claim 16 , wherein the divergent portion has a flatness defined, in a streamwise direction, by a curve having a second derivative with a magnitude of less than 0.005 inch −1 extending from the throat, and wherein said generating a disturbance includes generating a disturbance at a predetermined location selected to create a flow separation zone extending substantially from the throat to the downstream end of the nozzle.

18. The method of claim 16 , further comprising using a zero-net max flux jet to cause the flow separation.

19. The method of claim 18 , wherein the zero-net max flux jet is a synthetic jet and wherein said generating a disturbance by the disturbance generator comprises generating pulses with the synthetic jet at a pulse frequency of at least 20*(1/T) Hz.

20. A method for thrust vectoring comprising:
accelerating a flow to supersonic speed by passing a flow through a convergent-divergent nozzle, the convergent-divergent nozzle including a sharp throat, a total angle between convergent and divergent portions of the nozzle of less than 150°, and a divergence angle of the divergent portion of at least 12°, the convergent-divergent nozzle further including a disturbance generator located on the divergent portion; and
generating a disturbance by the disturbance generator to induce shockless flow separation from a wall of the divergent portion wherein the disturbance generator includes an injection slot; and,
injecting up to about 0.2% of total exhaust flow through the injection slot to provide a vectoring effectiveness of greater than 8.0.

21. The method of claim 16 , wherein the disturbance generator includes an injection slot, the method further comprising injecting a range of 0.2% to 2.6% of total exhaust flow to produce a range of vectoring effectiveness from 8.5 to 2.9.

Assignees

• Boeing Co

Inventors

• Winkler Chad M
• Dorgan Andrew J
• Werner Eric L

Classifications

• F02K1/28 Primary

  using fluid jets to influence the jet flow · CPC title

• F02K1/002

  with means to modify the direction of thrust vector (F02K1/54 takes precedence; thrust vectoring of rockets F02K9/80) · CPC title