Liquid rocket engine assemblies and related methods

Patent metadata

Field	Value
Publication number	US-11846256-B2
Application number	US-202117318167-A
Country	US
Kind code	B2
Filing date	May 12, 2021
Priority date	Nov 14, 2016
Publication date	Dec 19, 2023
Grant date	Dec 19, 2023

Abstract

A liquid rocket engine assembly comprising a thrust chamber, a nozzle, and a joint structure. The joint structure attaches the thrust chamber and the nozzle and comprises at least one seal element and an attachment ring interposed between the thrust chamber and the nozzle. Fasteners extend between the nozzle and the thrust chamber through the at least one seal element and the attachment ring. Materials of the thrust chamber and of the nozzle comprise different coefficients of thermal expansion. A method of forming a liquid rocket engine assembly is also disclosed.

First claim

What is claimed is:

1. A joint structure for attaching a thrust chamber and a nozzle of a rocket engine assembly, the joint structure comprising:
two seal elements configured to be interposed between the thrust chamber and the nozzle;
an insulation ring configured to be disposed between the two seal elements, the insulation ring comprising an angled surface configured to partially maintain a seal between the thrust chamber and the nozzle;
an attachment ring configured to be disposed circumferentially around the thrust chamber and adjacent to an aft of the insulation ring; and
fasteners configured to extend through the attachment ring and both seal elements of the two seal elements and to secure the joint structure to the thrust chamber and to the nozzle.

2. The joint structure of claim 1 , wherein at least one seal element of the two seal elements or the attachment ring comprises an annular shape.

3. The joint structure of claim 1 , wherein at least one seal element of the two seal elements comprises a flexible material.

4. The joint structure of claim 1 , wherein the attachment ring is separate and discrete from the nozzle, and wherein a flange element forms an integral part of the thrust chamber.

5. The joint structure of claim 1 , further comprising a support ring laterally adjacent to the insulation ring and disposed at least partially between the two seal elements.

6. The joint structure of claim 1 , further comprising a flange element of the thrust chamber, wherein the fasteners are configured to extend through the attachment ring, through both seal elements of the two seal elements, and into the flange element of the thrust chamber.

7. The joint structure of claim 6 , wherein the attachment ring and the flange element are at least partially aligned in a direction at least substantially parallel to a longitudinal axis of the rocket engine assembly.

8. The joint structure of claim 1 , wherein the fasteners, when extending through the attachment ring and both seal elements of the two seal elements, extend in a direction at least substantially parallel to a longitudinal axis of the rocket engine assembly.

9. A method of forming a liquid rocket engine assembly, the method comprising:
placing a joint structure comprising two substantially flat seal elements including holes around an outer circumference thereof, an insulation ring, and an attachment ring at least partially between a nozzle and a thrust chamber, comprising:
interposing the two seal elements at least partially between the thrust chamber and the nozzle;
disposing the insulation ring between the two seal elements; and
disposing the attachment ring circumferentially around the thrust chamber and adjacent to an aft of the insulation ring; and

inserting fasteners through the holes in the attachment ring and both seal elements of the two seal elements.

10. The method of claim 9 , further comprising positioning a support ring laterally adjacent to the insulation ring and at least partially between the two seal elements.

11. The method of claim 9 , wherein inserting fasteners comprises inserting the fasteners completely through the attachment ring and both seal elements of the two seal elements and at least partially into a flange of the thrust chamber.

12. The method of claim 9 , wherein inserting fasteners comprises inserting the fasteners to extend in a direction at least substantially parallel to a longitudinal axis of the liquid rocket engine assembly.

13. A liquid rocket engine assembly, comprising:
a thrust chamber;
a nozzle; and
a joint structure disposed at least partially between the thrust chamber and the nozzle, the joint structure attaching the thrust chamber and the nozzle, the joint structure comprising:
an attachment ring disposed circumferentially around the thrust chamber;
a flange element of the thrust chamber;
two substantially flat seal elements, including holes around an outer circumference thereof, interposed at least partially between the thrust chamber and the nozzle and at least partially between the thrust chamber and the attachment ring;
an insulation ring disposed between the two seal elements; and
fasteners extending through the attachment ring and the holes of the two seal elements and securing the joint structure to the thrust chamber and to the nozzle.

14. The liquid rocket engine assembly of claim 13 , further comprising a support ring laterally adjacent to the insulation ring and disposed at least partially between the two seal elements.

15. The liquid rocket engine assembly of claim 13 , wherein the attachment ring is separate and discrete from the nozzle, and wherein the flange element forms an integral part of the thrust chamber.

16. The liquid rocket engine assembly of claim 13 , wherein the attachment ring and the flange element are at least partially aligned in a direction at least substantially parallel to a longitudinal axis of the liquid rocket engine assembly.

17. The liquid rocket engine assembly of claim 13 , wherein the fasteners extend in a direction at least substantially parallel to a longitudinal axis of the liquid rocket engine assembly.

Assignees

• Northrop Grumman Systems Corp

Inventors

• Shigley John K
• George Russell J
• Neunzert Martin
• Mcculley Martin
• Hernandez Marc
• Roberts Robert K
• Breitenbach Lauren F
• Cramer Klaron

Classifications

• F02K9/97 Primary

  Rocket nozzles (thrust or thrust vector control F02K9/80) · CPC title

• F02K9/34

  Casings; Combustion chambers; Liners thereof · CPC title

• F02K9/343

  Joints, connections, seals therefor · CPC title

• F02K9/60

  Constructional parts; Details not otherwise provided for · CPC title

• F02K9/62

  Combustion or thrust chambers · CPC title