Enhanced liquid oxygen-propylene rocket engine

Patent metadata

Field	Value
Publication number	US-10072612-B2
Application number	US-201615285324-A
Country	US
Kind code	B2
Filing date	Oct 4, 2016
Priority date	Oct 5, 2015
Publication date	Sep 11, 2018
Grant date	Sep 11, 2018

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 propellant injection apparatus, comprising:
an injector assembly formed into a single body by an additive manufacturing process and comprising:
a fuel cavity;
an oxidizer cavity that forms a quasi-toroidal shape around the fuel cavity;
two or more propellant feed stubs forming tube structures tapered outwards from a first face of the injector assembly and formed into the single body of the injector assembly by the additive manufacturing process, wherein the two or more propellant feed stubs are each mechanically swaged or flared to mate with compression-type fittings in a metal-to-metal seal for attachment to associated propellant feed lines, with at least a first stub configured to carry fuel through a first channel to the fuel cavity and at least a second stub configured to carry oxidizer through a second channel to the oxidizer cavity; and
a plurality of injection features comprising a plurality of 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 plurality of apertures, with ones of the plurality of injection features configured to inject the fuel and the oxidizer for combustion;
wherein the first propellant feed stub extends outward from a central position of the first face of the injector assembly, and the second stub extends outward from the first face of the injector assembly in a position offset from the central position, and flow passages of the injector assembly are sized to account for a change in density of using densified propylene cooled below 25° C. as the fuel and liquid oxygen as the oxidizer.

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

3. The apparatus of claim 1 , comprising:
the plurality of injection features formed into the single body by the additive manufacturing process.

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

5. The apparatus of claim 4 , comprising:
the plurality of injection features comprising a second portion of orifices configured to inject fuel directed outward at the associated combustion chamber wall for cooling of the associated combustion chamber wall.

6. A liquid rocket engine, comprising:
a combustion chamber configured to receive liquid oxygen and liquid propylene for combustion;
a first propellant feed line configured to carry the liquid oxygen from a first propellant tank to a first main valve;
a second propellant feed line configured to carry the liquid propylene from a second propellant tank to a second main valve;
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 single body by an additive manufacturing process and comprising:
a fuel cavity;
an oxidizer cavity that forms a quasi-toroidal shape around the fuel cavity;
two or more propellant feed stubs forming tube structures tapered outwards from a first face of the injector assembly and formed into the single body of the injector assembly by the additive manufacturing process, wherein the two or more propellant 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 propellant feed line routed from the associated ones of the first and second main valves, with at least a first stub configured to carry the liquid propylene to the fuel cavity and at least a second stub configured to carry the liquid oxygen to the oxidizer cavity; and
a plurality of injection features comprising a plurality of 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 plurality of apertures, with ones of the plurality of injection features configured to inject the liquid oxygen and the liquid propylene into the combustion chamber for combustion;
wherein the first propellant feed stub extends outward from a central position of the first face of the injector assembly, and the second stub extends outward from the first face of the injector assembly in a position offset from the central position, and flow passages of the injector assembly are sized to account for a change in density of using densified propylene cooled below 25° C. as the fuel and liquid oxygen as the oxidizer.

7. The liquid rocket engine of claim 6 , comprising:
the injector assembly comprising an aluminum material that forms the single body by the additive manufacturing process.

8. The liquid rocket engine of claim 6 , comprising;
the plurality of injection features formed into the single body by the additive manufacturing process, and comprising a first portion of orifices configured to inject fuel and oxidizer in a generally conical shape directed towards a centerline of the combustion chamber.

9. The liquid rocket engine of claim 8 , comprising:
the plurality of injection features comprising a second portion of orifices configured to inject fuel directed outward at a wall of the combustion chamber for cooling of the wall of the combustion chamber.

10. The liquid rocket engine of claim 6 , comprising:
a first bleed valve coupled to the first propellant feed line before the first main valve and configured to selectively evacuate at least a portion of vaporized liquid oxygen within the first propellant feed line; and
a second bleed valve coupled to the second propellant feed line before the second main valve and configured to selectively evacuate at least a portion of vaporized liquid propylene within the second propellant feed line.

11. The liquid rocket engine of claim 6 , comprising:
a first propellant tank configured to store the liquid oxygen in a cryogenic state prior to ignition of the liquid rocket engine; and
a second propellant tank configured to store the liquid propylene in a densified state prior to the ignition of the liquid rocket engine.

12. A method of manufacturing a rocket engine propellant injection apparatus, the method comprising:
forming an injector assembly into single body by an additive manufacturing process, wherein the single 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 propellant feed stub into a first face of the single body and tapering outwards from a central position on the first face of the single body by the additive manufacturing process to provide a first channel to carry fuel to the fuel cavity;
forming at least a second propellant feed stub into the first face of the single body and tapering outwards from a position offset from the central position on the first face of the single body by the additive manufacturing process to provide a second channel to carry oxidizer to the oxidizer cavity;
forming a plurality of propellant injection features into the single body by the additive manufacturing process comprising apertures in a second face of the injector assembly opposite the first face of the injector assembly, and sizing flow passages of the injector assembly to account for a change in density of using densified propylene cool

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

• B33Y10/00

  Processes of additive manufacturing · CPC title