Enhanced liquid oxygen-propylene rocket engine

Patent metadata

Field	Value
Publication number	US-2017096967-A1
Application number	US-201615285324-A
Country	US
Kind code	A1
Filing date	Oct 4, 2016
Priority date	Oct 5, 2015
Publication date	Apr 6, 2017
Grant date	—

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 single body by an additive manufacturing process and comprising: a fuel cavity; an oxidizer cavity; one or more propellant feed stubs protruding from the injector assembly and formed into the single body of the injector assembly 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; and a plurality of injection features comprising by apertures in a face of the injector assembly, ones of the plurality of injection features configured to inject the fuel and the oxidizer for combustion.

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 , wherein the rocket engine propellant injection apparatus is configured to employ densified propylene as the fuel and liquid oxygen as the oxidizer.

4 . The apparatus of claim 1 , comprising:
the one or more propellant feed stubs forming tube structures tapered outwards from a first face of the injector assembly and configured to mate with compression-type fittings for attachment to associated propellant feed lines.

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

6 . 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.

7 . The apparatus of claim 6 , 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.

8 . 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 single body by an additive manufacturing process and comprising:
a fuel cavity;
an oxidizer cavity;
one or more propellant feed stubs protruding from the injector assembly and formed into the single body of the injector assembly by the additive manufacturing process, 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 by apertures in a face of the injector assembly, ones of the plurality of injection features configured to inject the liquid oxygen and the liquid propylene into the combustion chamber for combustion.

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

10 . The liquid rocket engine of claim 8 , wherein the liquid propylene comprises densified propylene cooled below at least one of an ambient temperature and an atmospheric boiling point of propylene.

11 . The liquid rocket engine of claim 8 , comprising:
the one or more propellant feed stubs forming tube structures outwards from a first face of the injector assembly, the first face opposite a face of the injector assembly comprising the plurality of injection features.

12 . The liquid rocket engine of claim 8 , comprising:
the one or more propellant feed stubs configured to mate with compression-type fittings for attachment to associated propellant feed lines routed from the associated ones of the first and second main valves.

13 . The liquid rocket engine of claim 8 , 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.

14 . The liquid rocket engine of claim 13 , 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.

15 . The liquid rocket engine of claim 8 , 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.

16 . The liquid rocket engine of claim 8 , 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.

17 . 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; forming at least a first propellant feed stub into 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 single body by the additive manufacturing process to provide a second channel to carry oxidizer to the oxidizer cavity; and forming a plurality of propellant injection features into the single body by the additive manufacturing process comprising apertures in a face of the injector assembly.

18 . The method of claim 17 , further comprising:
forming the injector assembly into the single body using an aluminum material in the additive manufacturing process.

19 . The method of claim 17 , further comprising:
attaching a first compression fitting to the first propellant feed stub and a second compression fitting to the second propellant feed stub, the first and second compression fittings configured to couple to associated propellant lines.

20 . The method of claim 17 , further comprising:
forming the plurality of injection features to include a first portion of directional orifices configured to inject fuel and oxidizer in a generally conical shape directed towards a centerline of a combustion chamber, and a second portion of directional orifices configured to inject fuel directed outward at a wall of the combustion chamber.

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

• B22F10/28

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

• B22F10/14

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

• F02K9/566

  elements and safety devices, e.g. pressure relief valves · CPC title

• B22F3/008

  Operations & Transport · mapped topic