Combustion device test apparatus and method

Patent metadata

Field	Value
Publication number	US-11015806-B2
Application number	US-201615343272-A
Country	US
Kind code	B2
Filing date	Nov 4, 2016
Priority date	Nov 4, 2016
Publication date	May 25, 2021
Grant date	May 25, 2021

Abstract

A combustion device test apparatus including a combustion device, a holding station configured to hold the combustion device, a fuel supply conduit, and a pressure wave fuse coupling the fuel supply conduit to the combustion device, the pressure wave fuse being frictionally coupled to one or more of the combustion device and the fuel supply conduit at a frictional coupling such that the pressure wave fuse is configured to disengage one or more of the combustion device and the fuel supply conduit at the frictional coupling upon traversal of a flame front pressure wave through the pressure wave fuse.

First claim

What is claimed is:

1. A combustion device test apparatus comprising:
a micro thruster test article;
a holding station configured to hold the micro thruster test article;
a fuel supply conduit; and
a pressure wave fuse coupling the fuel supply conduit to the micro thruster test article, the pressure wave fuse being frictionally coupled to the micro thruster test article and the fuel supply conduit at a frictional coupling such that the pressure wave fuse is configured to resiliently expand so that expansion of the pressure wave fuse and a gas flow at the frictional coupling between the pressure wave fuse and one or more of the micro thruster test article and the fuel supply conduit releases the frictional coupling to disengage the pressure wave fuse from the one or more of the micro thruster test article and the fuel supply conduit at the frictional coupling upon traversal of a flame front pressure wave through the pressure wave fuse;
wherein the fuel supply conduit is configured to provide a mixture of propellants and the fuel supply conduit comprises one or more of a mixing valve and a metering valve.

2. The combustion device test apparatus of claim 1 , wherein the pressure wave fuse comprises a transparent conduit.

3. The combustion device test apparatus of claim 1 , wherein the pressure wave fuse comprises a flexible conduit.

4. The combustion device test apparatus of claim 1 , wherein the mixture of propellants includes a mixture of gaseous propellants.

5. The combustion device test apparatus of claim 1 , wherein the mixture of propellants includes a mixture of liquid propellants.

6. The combustion device test apparatus of claim 1 , wherein the mixture of propellants includes a mixture of gaseous and liquid propellants.

7. The combustion device test apparatus of claim 1 , further comprising an exhaust device disposed adjacent the pressure wave fuse, the exhaust device being configured to vent ambient atmosphere surrounding at least the pressure wave fuse.

8. The combustion device test apparatus of claim 1 , wherein the pressure wave fuse comprises a conduit having a first end and a second end, at least one of the first and the second end having a frictional coupling surface configured to frictionally engage a respective one of the micro thruster test article and the fuel supply conduit.

9. The combustion device test apparatus of claim 1 , further comprising an ignitor disposed adjacent the holding station, the ignition source being movably mounted with respect to the holding station such that a distance between the ignition source and the micro thruster test article is variable, the ignition source being configured to ignite propellants from the micro thruster test article.

10. The combustion device test apparatus of claim 1 , further comprising an automated valve configured to stop a flow of fuel through the fuel supply conduit upon separation of the pressure wave fuse from one or more of the fuel supply conduit and the micro thruster test article.

11. A combustion device test apparatus comprising:
a micro thruster test article;
a fuel supply conduit;
a pressure wave fuse comprising a conduit having a first end and a second end, the conduit being configured to transport fuel between the fuel supply conduit and the micro thruster test article; and
an automated valve configured to stop a flow of fuel through the fuel supply conduit upon separation of the pressure wave fuse from one or more of the fuel supply conduit and the micro thruster test article;
wherein at least one of the first end and the second end of the conduit includes a frictional coupling surface that is configured to frictionally engage a respective one of the fuel supply conduit and the micro thruster test article at a frictional coupling, the frictional coupling surface being configured to resiliently expand so that the frictional coupling surface of the at least one of the first end and the second end of the pressure wave fuse expands to and a gas flow between the frictional coupling surface the respective one of the fuel supply conduit and the micro thruster test article disengages the pressure wave fuse from the respective one of the fuel supply conduit and the micro thruster test article at the frictional coupling upon traversal of a flame front pressure wave through the pressure wave fuse.

12. The combustion device test apparatus of claim 11 , wherein the fuel supply conduit is configured to provide a mixture of propellants.

13. The combustion device test apparatus of claim 12 , wherein the fuel supply conduit comprises one or more of a mixing valve and a metering valve.

14. The combustion device test apparatus of claim 11 , further comprising a holding station configured to hold the micro thruster test article.

15. A method of testing a micro thruster test article, the method comprising:
coupling a first end of a pressure wave fuse to a micro thruster test article at a first coupling; and
coupling a second end of the pressure wave fuse to a fuel supply conduit at a second coupling, where at least one of the first coupling and the second coupling are frictional couplings;
wherein:
the pressure wave fuse expands so that expansion of the pressure wave fuse and a gas flow at one or more of the first coupling and the second coupling between the pressure wave fuse and one or more of the micro thruster test article and the fuel supply conduit releases the one or more of the first coupling and the second coupling to automatic disengage the pressure wave fuse from the one or more of the first coupling and the second coupling in response to a flame front pressure wave travelling through the pressure wave fuse, and
the fuel supply conduit is configured to provide a mixture of propellants and the fuel supply conduit comprises one or more of a mixing valve and a metering valve.

16. The method of claim 15 , further comprising determining boundary conditions of the micro thruster test article operation using fuel provided through the fuel supply conduit.

17. The method of claim 16 , further comprising flowing a premixed propellant from the fuel supply conduit to the micro thruster test article through the pressure wave fuse.

18. The method of claim 16 , further comprising varying an internal diameter of the pressure wave fuse depending on a predetermined flow rate of propellant to the micro thruster test article.

19. The method of claim 15 , further comprising automatically arresting a flow of propellant through the fuel supply conduit upon disengagement of the pressure wave fuse from one or more of the first coupling and second coupling.

Assignees

• Boeing Co

Inventors

• Reid Phillip C
• Peterson William G

Classifications

• F23K2900/05001

  Control or safety devices in gaseous or liquid fuel supply lines · CPC title

• F23N5/247 Primary

  using mechanical means · CPC title

• F23N2231/28

  preventing flash-back or blow-back · CPC title