Fragmenting nozzle system

Patent metadata

Field	Value
Publication number	US-10690091-B2
Application number	US-201615762735-A
Country	US
Kind code	B2
Filing date	Oct 19, 2016
Priority date	Nov 6, 2015
Publication date	Jun 23, 2020
Grant date	Jun 23, 2020

Abstract

A rocket motor includes a case and first and second nozzles in the case. The first nozzle is disposed in the second nozzle. The first nozzle includes a forward leg, a rear leg, and an intermediate leg. The intermediate leg has a convex conical geometry, and the forward leg has a forward lip that is spaced from the case. The rear leg has a rear lip that is spaced from the case. The forward leg and the rear leg at least partially define a flow passage through the first nozzle. The first nozzle is exclusively secured by the intermediate leg to at least one of the case or the second nozzle. At least a portion of a fragmentation system is disposed between the first and second nozzles.

First claim

What is claimed is:

1. A nozzle system comprising:
an outer nozzle;
an inner nozzle radially within the outer nozzle and circumscribing an axis, the nozzle being formed of a brittle material and having a convergent leg, a divergent leg, a throat section that the convergent leg narrows to and the divergent leg expands from and an intermediate leg between the convergent leg and the divergent leg, the convergent leg and the divergent leg at least partially defining a flow passage through the nozzle; and
an ignition system including an energetic material disposed along the intermediate leg and the convergent leg, wherein the energetic material produces a pressure wave upon activation, the pressure wave breaking apart the inner nozzle.

2. The nozzle system as recited in claim 1 , wherein the intermediate leg has a convex conical surface.

3. The nozzle system as recited in claim 1 , wherein the brittle material selected from the group consisting of ceramic materials, graphite materials, and combinations thereof.

4. The nozzle system as recited in claim 1 , wherein the energetic material is in contact with the intermediate leg and the convergent leg and is radially adjacent the neck section.

5. A rocket motor comprising:
a case;
a nozzle system including first and second nozzles disposed in the case, the first nozzle at least partially disposed in the second nozzle, the first nozzle including:
a forward leg, a rear leg, and an intermediate leg between the forward leg and the rear leg, wherein the intermediate leg has a convex conical geometry,
wherein the forward leg is spaced radially away from the case such that there is a forward gap between a forward lip of the forward leg and the case,
wherein the rear leg has a rear lip that is spaced from the case such that there is a rear gap between the rear lip and the case,
the forward leg and the rear leg at least partially defining a flow passage through the first nozzle for gases to enter at the forward leg and exit at the rear leg; and

wherein the first nozzle is exclusively secured by the intermediate leg to at least one of the case or the second nozzle,
a fragmentation system, at least a portion of which is disposed between the first and second nozzles.

6. The rocket motor as recited in claim 5 , wherein the forward gap is radially larger than the rear gap.

7. The rocket motor as recited in claim 5 , wherein the intermediate leg has an intermediate lip that is axially closer to the rear lip than to the forward lip.

8. The rocket motor as recited in claim 5 , wherein the first nozzle is formed of a material selected from the group consisting of ceramic materials, graphite materials, and combinations thereof.

9. The rocket motor as recited in claim 5 , wherein the fragmentation system includes an energetic material disposed between the first and second nozzles.

10. The rocket motor as recited in claim 9 , wherein the energetic material abuts the intermediate leg.

11. The rocket motor as recited in claim 9 , wherein the energetic material is disposed between the forward leg and the intermediate leg.

12. The rocket motor as recited in claim 5 , wherein the forward leg, the intermediate leg, and the second nozzle bound a void volume.

13. The rocket motor as recited in claim 5 , wherein the fragmentation system includes an energetic material that is in contact with the forward leg and the intermediate leg.

14. The rocket motor as recited in claim 13 , wherein the forward leg converges to a neck section, the rear leg diverges from the neck, and the energetic material is radially adjacent the neck section.

15. The rocket motor as recited in claim 5 , wherein the fragmentation system includes an energetic material that produces a pressure wave upon activation, the pressure wave breaking apart the first nozzle.

Assignees

• Aerojet Rocketdyne Inc

Inventors

• Stracener Phillip
• Derstine Mark S
• Mendillo John

Classifications

• F02K9/974

  Nozzle- linings; Ablative coatings · CPC title

• F05D2220/10

  in ram-jet engines or ram-jet driven vehicles · CPC title

• F02K9/978 Primary

  Closures for nozzles; Nozzles comprising ejectable or discardable elements · CPC title

• F02K9/32

  Constructional parts; Details not otherwise provided for · CPC title

• F02K9/97

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