Gas augmented rocket engine

• US 20070163228A1
• Filed: 01/19/2006
• Published: 07/19/2007
• Est. Priority Date: 01/19/2006
• Status: Abandoned Application

• Current Assignee: United Technologies Corporation (Rtx Corporation)
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Brown, William, Schilhavy, Peter
• Application Number:
  US11/334,965
• Publication Number:
  US 20070163228A1
• Time in Patent Office: Days
• US Class Current: 60/210
• CPC Class Codes: F02K 9/42 using liquid or gaseous propellants F02K9/72 takes precedence
• CPC Class Codes: F02K 9/64 having cooling arrangements
• CPC Class Codes: F02K 9/82 by injection of a secondary fluid into the rocket exhaust gases
• CPC Class Codes: F02K 9/972 Fluid cooling arrangements for nozzles F02K9/64 takes precedence
• CPC Class Codes: F05D 2260/202 by film cooling

Abstract

A rocket engine with an augmentation gas system that improves performance of the hypergolic combustion process. The augmentation gas system includes an acoustic cavity manifold mounted between an outer perimeter of an injector face and the combustion chamber. The augmentation gas system injects an augmentation gas active element such as hydrogen or an inactive element such as helium to provide significantly enhanced boundary layer coolant effect to reduce heat loading on the combustion chamber wall and enhance the specific impulse of the rocket engine.

Claims

1. An acoustic cavity manifold for a rocket engine comprising:

a multitude of axially extending acoustic cavities defined about a thrust axis;

a multitude of augmentation gas openings in communication with each of said multitude of acoustic cavities; and

a circumferential distribution manifold defined about said axis, said circumferential distribution manifold in communication with each of said multitude of augmentation gas openings.

2. The manifold as recited in claim 1, wherein said circumferential distribution manifold includes a circumferential channel defined within a radially extending acoustic cavity manifold ring.

3. The manifold as recited in claim 2, wherein said radially extending acoustic cavity manifold ring radially extends from a cylindrical body.

4. The manifold as recited in claim 3, wherein said multitude of axially extending acoustic cavities are defined within an inner surface of said cylindrical body and extend from said multitude of axially extending acoustic cavities.

5. A rocket engine comprising:

an injector assembly;

a combustion chamber mounted to said injector assembly, said combustion chamber defined about a thrust axis; and

an acoustic cavity manifold mounted to said injector assembly, said acoustic cavity manifold in communication with said combustion chamber.

6. The rocket engine as recited in claim 5, wherein said acoustic cavity manifold is mounted about an outer perimeter of an injector face of said injector assembly.

7. The rocket engine as recited in claim 5, wherein said acoustic cavity manifold includes a multitude of augmentation gas openings directed along a combustion chamber wall.

8. The rocket engine as recited in claim 5, wherein said acoustic cavity manifold defines a multitude of axially extending acoustic cavities defined about said thrust axis.

9. The rocket engine as recited in claim 8, wherein said multitude of axially extending acoustic cavities are axially aligned with a combustion chamber wall of said combustion chamber.

10. The rocket engine as recited in claim 5, wherein said injector assembly communicates an oxidizer and a fuel to said combustion chamber.

11. The rocket engine as recited in claim 5, further comprising a bi-propellant valve system linked to an augmentation gas supply system to provide for the synchronized introduction of augmentation gas, oxidizer and fuel into said combustion chamber.

12. The rocket engine as recited in claim 11, further comprising an augmentation gas introduction valve of said augmentation gas supply system driven by a valve power piston of said bi-propellant valve system.

13. The rocket engine as recited in claim 12, further comprising a pilot valve in communication with said augmentation gas, electrical operation of said pilot valve operable to selectively communicate said augmentation gas to said valve power piston which drives a bi-propellant main stage valve of said bi-propellant valve system.

14. The rocket engine as recited in claim 13, wherein operation of said valve pilot system permits selective communication of said augmentation gas to said acoustic cavity manifold through said augmentation gas introduction valve.

15. A method of increasing the specific impulse efficiency of a rocket engine comprising the steps of:

(A) injecting an augmentation gas into a combustion chamber through an acoustic cavity manifold along a combustion chamber wall defined about a thrust axis.

16. A method as recited in claim 15, wherein said step (A) further comprises:

(a) generating a flow vector with the augmentation gas in-line with the combustion chamber wall; and

(b) providing an augmentation gas boundary layer transition between the combustion gas flow and the combustion chamber wall

17. A method as recited in claim 15, wherein said step (A) further comprises:

(a) injecting helium as the augmentation gas.

18. A method as recited in claim 15, wherein said step (A) further comprises:

(a) injecting hydrogen as the augmentation gas.

19. A method as recited in claim 15, wherein said step (A) further comprises:

(a) injecting the augmentation gas into the acoustic cavity manifold at a pressure above a chamber pressure within the combustion chamber.

20. A method as recited in claim 15, further comprising the steps of:

(B) linking operation of a bi-propellant valve system to an augmentation gas introduction valve to provide synchronized injection of the augmentation gas, an oxidizer and a fuel into the combustion chamber.