Helical cross flow (HCF) pulse detonation engine

Patent metadata

Field	Value
Publication number	US-9726080-B2
Application number	US-201313886030-A
Country	US
Kind code	B2
Filing date	May 2, 2013
Priority date	Mar 30, 2009
Publication date	Aug 8, 2017
Grant date	Aug 8, 2017

Abstract

A helical cross flow pulse detonation engine.

First claim

What is claimed is:

1. A helical cross flow combustor pulse detonation engine comprising:
a cylindrical annular housing having an outer surface and an inner surface;
a pulse detonation combustor embedded within the cylindrical annular housing and comprising:
a helical cylindrical member confined between the outer surface and the inner surface of the cylindrical annular housing;
at least one inlet port extending into the helical cylindrical member from the outer surface of the cylindrical annular housing; and
a continuous annular slot extending from the helical cylindrical member to the inner surface of the cylindrical annular housing;

at least one valve configured and positioned to control flow of oxidizer into the helical cylindrical member through the at least one inlet port;
at least one resilient member configured and positioned to resiliently bias the at least one valve closed;
an actuation member configured and positioned to open the at least one valve; and
a nozzle configured and positioned to flow combustion gases from an exhaust region circumscribed by the cylindrical annular housing.

2. The helical cross flow pulse combustor pulse detonation engine of claim 1 , wherein the actuation member comprises a camshaft in operable contact with the at least one valve.

3. The helical cross flow pulse combustor pulse detonation engine of claim 1 , wherein the at least one inlet port comprises a plurality of inlet ports, and the at least one valve comprises a plurality of valves, one valve per each inlet port.

4. The helical cross flow pulse combustor pulse detonation engine of claim 3 , wherein the actuation member comprises at least one camshaft in operable contact with each valve of the plurality.

5. The helical cross flow pulse combustor pulse detonation engine of claim 1 , wherein the helical cylindrical member exhibits a pitch angle greater than zero degrees relative to a central axis of the helical cylindrical member.

6. The helical cross flow pulse combustor pulse detonation engine of claim 1 , wherein the helical cylindrical member comprises a helical-shaped tube.

7. The helical cross flow pulse combustor pulse detonation engine of claim 1 , wherein the at least one resilient member comprises at least one spring in contact with the at least one valve and at least one valve retaining structure.

8. The helical cross flow pulse combustor pulse detonation engine of claim 1 , wherein the actuation member comprises a camshaft having at least one lobe configured and positioned to control opening of the at least one valve.

9. The helical cross flow pulse combustor pulse detonation engine of claim 1 , further comprising at least one structure configured and positioned to prevent the combustion gases from exiting a front section of the helical cross flow combustor pulse detonation engine.

10. The helical cross flow pulse combustor pulse detonation engine of claim 1 , further comprising:
at least one additional pulse detonation combustor embedded within the cylindrical annular housing and comprising:
at least one additional helical cylindrical member confined between the outer surface and the inner surface of the cylindrical annular housing;
at least one additional inlet port extending into the at least one additional helical cylindrical member from the outer surface of the cylindrical annular housing; and
at least one additional continuous annular slot extending from the at least one additional helical cylindrical member to the inner surface of the cylindrical annular housing;

at least one additional valve configured and positioned to control flow of the combustion gases into the at least one additional helical cylindrical member through the at least one additional inlet port; and
at least one additional resilient member operatively associated with the actuation member and resiliently biasing the at least one additional valve closed.

11. A helical cross flow pulse combustor pulse detonation engine comprising:
at least one helical-shaped combustor tube confined within a thickness of a cylindrical annular housing and having a sidewall exhibiting each of at least one oxidizer inlet and a combustion gas outlet therein;
at least one valve assembly operatively associated with the at least one helical-shaped combustor tube and comprising:
at least one cylindrical valve switchable between a closed position preventing flow of oxidizer through the at least one oxidizer inlet and an open position permitting flow of the oxidizer through the at least one oxidizer inlet;
at least one spring configured and positioned to hold the at least one cylindrical valve in the closed position; and
at least one actuator configured and positioned to adjust the at least one cylindrical valve to the open position upon a triggering event;

a cylindrical exhaust region surrounded by and in fluid communication with the at least one helical-shaped combustor tube; and
a nozzle positioned at an end of the cylindrical exhaust region.

12. The helical cross flow pulse combustor pulse detonation engine of claim 11 , wherein the at least one helical-shaped combustor tube comprises a plurality of helical-shaped combustor tubes each wrapping at least one full revolution about a central axis of the cylindrical exhaust region.

13. The helical cross flow pulse combustor pulse detonation engine of claim 12 , wherein each of the plurality of helical-shaped combustor tubes exhibits a pitch angle greater than zero degrees with respect to a central axis thereof.

Assignees

• Orbital Atk Inc

Inventors

• Guinan Daniel P
• Gettinger Christopher D

Classifications

• F02C3/165 Primary

  the combustion chamber contributes to the driving force by creating reactive thrust · CPC title

• F23R7/00

  Intermittent or explosive combustion chambers · CPC title

• F02C5/12 Primary

  the combustion chambers having inlet or outlet valves, e.g. Holzwarth gas-turbine plants · CPC title

• F02K7/06

  with combustion chambers having valves · CPC title

• F02C5/04

  the combustion chambers being formed at least partly in the turbine rotor · CPC title