Pulse detonation combustor

Patent metadata

Field	Value
Publication number	US-2016102609-A1
Application number	US-201514815400-A
Country	US
Kind code	A1
Filing date	Jul 31, 2015
Priority date	Oct 9, 2014
Publication date	Apr 14, 2016
Grant date	—

Abstract

A pulse detonation combustor may include a valve and a tubular combustor wall, which forms an airflow inlet and a combustion chamber. The valve may be configured to selectively fluidly couple the airflow inlet with the combustion chamber. The valve may include a center body and an annular projection. The center body and the projection may be configured to sealingly engage with one another.

First claim

What is claimed is:

1 . A pulse detonation combustor, comprising:
a tubular combustor wall forming an airflow inlet and a combustion chamber; and a valve configured to selectively fluidly couple the airflow inlet with the combustion chamber, the valve including a center body and an annular projection, wherein the center body and the projection are configured to sealingly engage with one another.

2 . The combustor of claim 1 , wherein the valve includes an annular translating sleeve comprising the projection.

3 . The combustor of claim 2 , wherein the translating sleeve is configured to translate along a centerline of the combustor wall relative to the center body to selectively open and close the valve.

4 . The combustor of claim 2 , wherein the center body is attached to the combustor wall by one or more struts.

5 . The combustor of claim 2 , wherein the projection is configured to axially engage the center body.

6 . The combustor of claim 2 , further comprising an actuator configured to move the translating sleeve relative to the center body.

7 . The combustor of claim 1 , wherein
the projection is fixed; and at least a portion of the center body is configured to translate along a centerline of the combustor wall relative to the projection to selectively open and close the respective valve.

8 . The combustor of claim 7 , wherein the projection is configured into the combustor wall.

9 . The combustor of claim 7 , wherein the center body includes a translating portion and a fixed portion that is attached to the combustor wall by one or more struts.

10 . The combustor of claim 9 , further comprising an actuator configured to move the translating portion relative to the fixed portion.

11 . The combustor of claim 1 , further comprising a fuel injector and an igniter arranged with the combustion chamber.

12 . The combustor of claim 11 , wherein, during a step of a pulse detonation cycle, the air-valve is configured to fluidly couple the airflow inlet with the combustion chamber and the injector is configured to inject fuel into the combustion chamber.

13 . The assembly of claim 11 , wherein, during a step of a pulse detonation cycle, the valve is configured to fluidly decouple the airflow inlet from the combustion chamber and the igniter is configured to ignite a fuel-air mixture within the combustion chamber.

14 . The combustor of claim 1 , wherein the center body has a generally aerodynamically shaped cross-sectional geometry.

15 . The combustor of claim 1 , wherein the center body is attached to the combustor wall by a strut, and a fuel conduit extends through the strut and into the center body to a nozzle configured with the center body.

16 . A pulse detonation combustor, comprising:
a tubular combustor wall forming an airflow inlet and a combustion chamber; and a valve configured to selectively fluidly couple the airflow inlet with the combustion chamber, the valve including a fixed center body and an annular translating sleeve.

17 . The combustor of claim 16 , wherein the sleeve is configured to translate along a centerline of the combustor wall relative to the center body to selectively open and close the respective valve.

18 . The combustor of claim 16 , wherein the sleeve includes an annular ridge that projects radially inward, and the ridge is configured to axially engage the center body.

19 . The combustor of claim 16 , further comprising an actuator configured to move the sleeve relative to the center body.

20 . A pulse detonation combustor, comprising:
a tubular combustor wall forming an airflow inlet and a combustion chamber; and a valve including a center body and an annular projection fixed relative to the combustor wall, wherein at least a portion of the center body is configured to selectively
engage the projection to fluidly decouple the airflow inlet from the combustion chamber; and
disengage the projection to fluidly couple the airflow inlet with the combustion chamber.

Assignees

• United Technologies Corp

Inventors

• Hill James D
• Haas Martin
• Fowler Robert B
• Lovett Jeffery A
• Blinn Roger F

Classifications

• F23C15/00

  Apparatus in which combustion takes place in pulses influenced by acoustic resonance in a gas mass {(for generating combustion products of high pressure or high velocity F23R7/00; starting devices F23D11/42)} · CPC title

• F02C5/02 Primary

  characterised by the arrangement of the combustion chamber in the chamber in the plant (combustion chambers per se F23R) · CPC title

• F23R7/00

  Intermittent or explosive combustion chambers · CPC title

• F23C2200/00

  Combustion techniques for fluent fuel · CPC title

• F23C2205/00

  Pulsating combustion · CPC title