Liquid oxygen-propylene rocket injector

Patent metadata

Field	Value
Publication number	US-10316795-B2
Application number	US-201816101000-A
Country	US
Kind code	B2
Filing date	Aug 10, 2018
Priority date	Oct 5, 2015
Publication date	Jun 11, 2019
Grant date	Jun 11, 2019

Abstract

Provided herein are various improvements to rocket engine components and rocket engine operational techniques. In one example, a rocket engine propellant injection apparatus is provided that includes a manifold formed into a single body by an additive manufacturing process and comprising a fuel cavity and an oxidizer cavity. The manifold also includes one or more propellant feed stubs, the one or more propellant feed stubs protruding from the manifold and formed into the single body of the manifold by the additive manufacturing process, with at least a first stub configured to carry fuel to the fuel cavity and at least a second stub configured to carry oxidizer to the oxidizer cavity. The manifold also includes a plurality of injection features formed by apertures in a face of the manifold, ones of the plurality of injection features configured to inject the fuel and the oxidizer for combustion.

First claim

What is claimed is:

1. A rocket engine injector apparatus, comprising:
an injector body formed by an additive manufacturing process;
a fuel cavity in the injector body;
an oxidizer cavity that forms a quasi-toroidal shape around the fuel cavity;
feed stubs formed into the injector body by the additive manufacturing process, the feed stubs comprising tube structures projecting outwards from a first face of the injector body and having swaged or flared features to mate with compression-type fittings in a metal-to-metal seal for attachment to associated feed lines;
wherein at least a first feed stub of the feed stubs extends outward from a first position on the first face of the injector body and is configured to carry fuel through a first channel to the fuel cavity;
wherein at least a second feed stub of the feed stubs extends outward from the first face of the injector body in a position offset from the first position and is configured to carry oxidizer through a second channel to the oxidizer cavity; and
a plurality of injection apertures in a second face of the injector body opposite the first face of the injector body configured to inject the fuel and the oxidizer for combustion, with each of the fuel cavity and the oxidizer cavity feeding a corresponding subset of the plurality of injection apertures.

2. The apparatus of claim 1 , wherein flow passages of at least the injector body are sized to account for densified propylene as the fuel and liquid oxygen as the oxidizer.

3. The apparatus of claim 2 , wherein the density of the densified propylene corresponds to propylene subcooled below an atmospheric boiling point of propylene.

4. The apparatus of claim 1 , comprising:
the injector body comprising an aluminum material that forms a single body by the additive manufacturing process.

5. The apparatus of claim 1 , comprising:
the plurality of injection apertures formed into the injector body by the additive manufacturing process.

6. The apparatus of claim 1 , comprising:
the plurality of injection apertures comprising a first portion configured to inject fuel and oxidizer in a generally conical shape directed inward with respect to an associated combustion chamber wall.

7. The apparatus of claim 6 , comprising:
the plurality of injection apertures comprising a second portion configured to inject fuel directed outward at the associated combustion chamber wall for cooling of the associated combustion chamber wall.

8. A rocket engine, comprising:
a combustion chamber configured to receive liquid oxygen and liquid propylene;
a first feed line configured to carry the liquid oxygen from a first tank to a first main valve;
a second feed line configured to carry the liquid propylene from a second tank to a second main valve; and
an injector assembly configured to receive the liquid oxygen and the liquid propylene from associated ones of the first and second main valves and inject the liquid oxygen and the liquid propylene into the combustion chamber, the injector assembly formed into a body by an additive manufacturing process and comprising:
a fuel cavity;
an oxidizer cavity that forms a quasi-toroidal shape around the fuel cavity;
feed stubs forming tube structures tapered outwards from a first face of the injector assembly and formed into the body of the injector assembly by the additive manufacturing process, wherein the feed stubs are each mechanically swaged or flared to mate with a compression-type fitting in a metal-to-metal seal for attachment to an associated feed line routed from the associated ones of the first and second main valves;
wherein at least a first stub extends outward from a first position on the first face of the injector assembly and is configured to carry the liquid propylene to the fuel cavity;
wherein at least a second stub extends outward from the first face of the injector assembly in a position offset from the first position and is configured to carry the liquid oxygen to the oxidizer cavity; and
injection apertures in a second face of the injector assembly opposite the first face of the injector assembly, each of the fuel cavity and the oxidizer cavity feeding a corresponding subset of the injection apertures, with corresponding ones of the injection apertures configured to inject the liquid oxygen and the liquid propylene into the combustion chamber for combustion.

9. The rocket engine of claim 8 , wherein flow passages of at least the injector assembly are sized to account for densified liquid propylene as a fuel and the liquid oxygen as an oxidizer.

10. The rocket engine of claim 9 , wherein the density of the densified liquid propylene corresponds to the liquid propylene subcooled below an atmospheric boiling point of propylene.

11. The rocket engine of claim 8 , comprising:
the injector assembly comprising an aluminum material that forms a single body by the additive manufacturing process.

12. The rocket engine of claim 8 , comprising:
the injection apertures formed into a single body by the additive manufacturing process, and comprising a first portion configured to inject fuel and oxidizer in a generally conical shape directed towards a centerline of the combustion chamber.

13. The rocket engine of claim 12 , comprising:
the injection apertures comprising a second portion configured to inject fuel directed outward at a wall of the combustion chamber for cooling of the wall of the combustion chamber.

14. The rocket engine of claim 8 , comprising:
a first bleed valve coupled to the first feed line before the first main valve and configured to selectively evacuate at least a portion of vaporized liquid oxygen within the first feed line; and
a second bleed valve coupled to the second feed line before the second main valve and configured to selectively evacuate at least a portion of vaporized liquid propylene within the second feed line.

15. The rocket engine of claim 8 , comprising:
a first tank configured to store the liquid oxygen in a cryogenic state prior to ignition of the rocket engine; and
a second tank configured to store the liquid propylene in a densified state prior to the ignition of the rocket engine.

16. A method comprising:
forming an injector assembly for a rocket engine into a body by an additive manufacturing process, wherein the body of the injector assembly comprises a fuel cavity and an oxidizer cavity that forms a quasi-toroidal shape around the fuel cavity;
forming at least a first feed stub into a first face of the body and tapering outwards from a central position on the first face of the body by the additive manufacturing process to provide a first channel to carry fuel to the fuel cavity;
forming at least a second feed stub into the first face of the body and tapering outwards from a position offset from the central position on the first face of the body by the additive manufacturing process to provide a second channel to carry oxidizer to the oxidizer cavity;
forming propellant injection features into the body by the additive manufacturing process in a second face of the injector assembly opposite the first face of the injector assembly; and
attaching a first compression fitting to the first feed stub and a second compression fitting to the second feed stub in a metal-to-metal seal, the first and second compression fittings each mechanically swaged or flared to couple to associated propellant lines.

17. The method of claim 16 , further comprising:
sizing flow passages of the injector assembly to account for a change in density of using liquid propylene as the fuel and liqu

Assignees

• Vector Launch Inc

Inventors

• Bostwick Christopher
• Garvey John
• Anderson Christopher
• Besnard Eric

Classifications

• B22F10/25

  Direct deposition of metal particles, e.g. direct metal deposition [DMD] or laser engineered net shaping [LENS] · CPC title

• B22F10/14

  by jetting of binder onto a bed of metal powder · CPC title

• B22F10/28

  Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM] · CPC title

• F02K9/52 Primary

  Injectors · CPC title

• Y02P10/295

  Cross-Sectional Technologies · mapped topic