Two-dimensional supersonic nozzle thrust vectoring using staggered ramps

Patent metadata

Field	Value
Publication number	US-11614050-B2
Application number	US-201816217370-A
Country	US
Kind code	B2
Filing date	Dec 12, 2018
Priority date	Jun 15, 2016
Publication date	Mar 28, 2023
Grant date	Mar 28, 2023

Abstract

A system and method for vectoring the thrust of a supersonic, air-breathing engine. A thrust vectoring mechanism uses two asymmetrically staggered ramps; one placed at the throat, the other positioned at the exit lip of the nozzle of the engine to re-direct exhaust flow off-axis with the nozzle.

First claim

What is claimed is:

1. An apparatus for vectoring thrust of an air-breathing engine comprising:
a Venturi nozzle having:
a converging section,
a throat,
a diverging section, and
an exit, arranged in series along a centerline of the Venturi nozzle from upstream to downstream, wherein a downstream end of the converging section ends at the throat and the diverging section diverges from the throat to the exit;

a first deployable ramp fixed to the nozzle at the throat; and
a single second deployable ramp fixed to the nozzle at the exit;
wherein:
the second deployable ramp is circumferentially arranged opposite the first deployable ramp;
a downstream terminus of the first deployable ramp is always upstream of the exit;
the first deployable ramp and the second deployable ramp each have a deployed state and an undeployed state;
the second deployable ramp extends downstream of the exit in the deployed state;
in the undeployed states of the first deployable ramp and the second deployable ramp, an exhaust flow is along the centerline; and
in the deployed states of the first deployable ramp and the second deployable ramp, the exhaust flow is deflected toward the centerline by the first deployable ramp and thereafter deflected by the second deployable ramp to thereby vector a thrust resulting from the exhaust flow off of the centerline.

2. The apparatus of claim 1 , wherein the first deployable ramp and the second deployable ramp are asymmetrically staggered.

3. The apparatus of claim 1 , wherein the air-breathing engine comprises a supersonic engine.

4. The apparatus of claim 1 , wherein:
the exhaust flow is axial when the first deployable ramp and the second deployable ramp are in the undeployed state; and
the exhaust flow is redirected to a non-axial condition when the first deployable ramp and the second deployable ramp are in the deployed state.

5. The apparatus of claim 4 , wherein:
the Venturi nozzle comprises a nozzle axis and the exhaust flow comprises a sonic line; and
the sonic line is skewed off-axis with the nozzle axis to vector thrust from the air-breathing engine when the first deployable ramp and/or the second deployable ramp are deployed.

6. The apparatus of claim 5 , wherein:
the first deployable ramp is configured to separate axial flow entering from the inlet; and
the second deployable ramp is configured to direct re-attaching airflow at the exit to an off-axis condition.

7. The apparatus of claim 4 , wherein at least one of the first deployable ramp and the second deployable ramp comprises a flap pivoting about a hinge from the undeployed state to the deployed state.

8. A thrust-vectored, air-breathing engine, comprising:
a Venturi nozzle having an inlet, an exit, and a throat disposed between the inlet and the exit, wherein the nozzle converges from the inlet to the throat and diverges from the throat to the exit;
a first deployable ramp fixed to the nozzle at the throat; and
a second deployable ramp fixed to the nozzle at the exit, opposite to and downstream of the first deployable ramp;
wherein:
a downstream terminus of the first deployable ramp is always upstream of the exit;
the first deployable ramp and the second deployable ramp each have a deployed state and an undeployed state;
the second deployable ramp extends downstream of the exit in the deployed state;
in the undeployed states of the first deployable ramp and the second deployable ramp, an exhaust flow is along the centerline; and
in the deployed states of the first deployable ramp and the second deployable ramp, the exhaust flow is deflected toward the centerline by the first deployable ramp and thereafter deflected by the second deployable ramp to thereby vector a thrust resulting from the exhaust flow off of the centerline.

9. The engine of claim 8 , wherein the first deployable ramp and the second deployable ramp are asymmetrically staggered.

10. The engine of claim 8 , wherein the thrust-vectored, air-breathing engine comprises a supersonic engine.

11. The engine of claim 8 , wherein:
the exhaust flow is axial when the first deployable ramp and the second deployable ramp are in the undeployed state; and
the exhaust flow is redirected to a non-axial condition when the first deployable ramp and the second deployable ramp are in the deployed state.

12. The engine of claim 11 , wherein:
the Venturi nozzle comprises a nozzle axis and the exhaust flow comprises a sonic line; and
the sonic line is skewed off-axis with the nozzle axis to vector thrust from the thrust-vectored, air-breathing engine when the first deployable ramp and/or the second deployable ramp are deployed.

13. The engine of claim 12 , wherein:
the first deployable ramp is configured to separate axial flow entering from the inlet; and
the second deployable ramp is configured to direct re-attaching airflow at the exit to an off-axis condition.

14. The engine of claim 11 , wherein at least one of the first deployable ramp and the second deployable ramp comprises a flap pivoting about a hinge from the undeployed state to the deployed state.

15. A method for vectoring thrust of an air-breathing engine comprising a Venturi nozzle having:
a converging section,
a throat,
a diverging section, and
an exit, arranged in series along a centerline of the Venturi nozzle from upstream to downstream, wherein a downstream end of the converging section ends at the throat and the diverging section diverges from the throat to the exit;
the method comprising:
deploying first and second deployable ramps within the Venturi nozzle; and
redirecting an exhaust flow of the Venturi nozzle;

wherein:
the second deployable ramp is circumferentially arranged opposite the first deployable ramp;
a downstream terminus of the first deployable ramp is always upstream of the exit;
the first deployable ramp and the second deployable ramp each have a deployed state and an undeployed state;
the second deployable ramp extends downstream of the exit in the deployed state;
in the undeployed states of the first deployable ramp and the second deployable ramp, an exhaust flow is along the centerline; and
in the deployed states of the first deployable ramp and the second deployable ramp, the exhaust flow is deflected toward the centerline by the first deployable ramp and thereafter deflected by the second deployable ramp to thereby vector a thrust resulting from the exhaust flow off of the centerline.

16. The method of claim 15 , wherein the first and second deployable ramps are asymmetrically staggered.

17. The method of claim 15 , wherein the air-breathing engine comprises a supersonic engine.

18. The method of claim 15 , wherein:
the exhaust flow is axial when the first and second deployable ramps are in the undeployed state; and
redirecting the exhaust flow comprises directing the exhaust flow to a non-axial condition by activating the first and second deployable ramps to the deployed state.

19. The method of claim 18 , wherein:
the Venturi nozzle comprises a nozzle axis and the exhaust flow comprises a sonic line; and
redirecting the exhaust flow comprises skewing the sonic line off-axis with the nozzle axis to vector thrust from the air-breathing engine.

20. The method of claim 19 , wherein:
deploying the first and second deployable ramps comprises deploying the first deployable ramp to separate axial flow entering from the inlet and deploying the second deployable ramp to direct re-attaching airflow at the exit to an off-axis c

Assignees

• Univ California

Inventors

• Montes Carlos F
• Davis Roger L

Classifications

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F02K1/1207

  of one series of flaps hinged at their upstream ends on a fixed structure (F02K1/1215 - F02K1/1292 take precedence) · CPC title

• F05D2250/73

  asymmetric · CPC title

• F05D2250/411

  in rotation · CPC title

• F02K1/006 Primary

  within one plane only · CPC title