Rotary valve multiple combustor pulse detonation engine

• US 5,345,758 A
• Filed: 04/14/1993
• Issued: 09/13/1994
• Est. Priority Date: 04/14/1993
• Status: Expired due to Term

• Current Assignee: Shocksystem Incorporated
• Original Assignee: Adroit Systems, Inc. (General Dynamics Corporation)
• Inventors: Bussing, Thomas R.
• Primary Examiner(s): Bertsch, Richard A.
• Assistant Examiner(s): RICHMAN, HOWARD
• Application Number:
  US08/045,771
• Time in Patent Office: 517 Days
• Field of Search: 431/1, 431/158, 431/278, 431/280, 431/281, 60/39.38, 60/39.39, 60/39.76, 60/39.78, 60/39.821, 60/39.826, 60/39.827
• US Class Current: 60/39.38
• CPC Class Codes: B01J 3/08 Application of shock waves for chemical reactions or for modifying the crystal structure of substances
• CPC Class Codes: B05B 7/0006 Spraying by means of explosions
• CPC Class Codes: C23C 4/126 Detonation spraying
• CPC Class Codes: F01D 5/288 Protective coatings for blades
• CPC Class Codes: F02K 7/06 with combustion chambers having valves
• CPC Class Codes: F02K 7/075 with multiple pulse-jet engines
• CPC Class Codes: F02K 9/972 Fluid cooling arrangements for nozzles F02K9/64 takes precedence
• CPC Class Codes: F02K 9/974 Nozzle- linings; Ablative coatings

Abstract

A pulse detonation engine is provided with several detonation combustors selectively coupled to an air inlet and fuel source by a rotary valve. The rotary valve isolates the steady operation of the air inlet and fuel system from the unsteady nature of the detonation process, and allows the fueling of some of the detonation chambers while detonation occurs in other detonation chambers. The fuel system may use a solid fueled gas generator.

Claims

1. A rotary valve multiple combustor pulse detonation engine comprising:

at least two detonation chambers, each having an inlet end and an outlet end;

a fuel manifold for supplying fuel from a fuel source to said at least two detonation chambers at said inlet ends;

an inlet air duct manifold for supplying air to said at least two detonation chambers at said inlet ends;

means for initiating a pulsed supersonic shock wave-triggered detonation combustion wave for initiating detonation in said at least two detonation chambers; and

a rotor disk valve having at least one opening and at least one solid portion, wherein said rotor disk valve is positioned between said inlet ends of said detonation chambers and said fuel and inlet air duct manifolds, wherein said rotor disk valve rotates so that said opening is positioned over said inlet end of one of said at least two detonation chambers to allow fuel and air to enter said detonation chamber, and wherein said rotor disk valve further rotates so that said solid portion is positioned over said inlet end of said one of said at least two detonation chambers so that said fuel and air inside said one of said at least two detonation chambers can be detonated by said means for initiating a pulsed supersonic shock wave-triggered detonation combustion wave.

2. The rotary valve multiple combustor pulse detonation engine of claim 1 further comprising:

a manifold mounting plate connected to said fuel manifold and said inlet air duct manifold; and

a combustor mounting plate connected to said at least two detonation chambers;

wherein said rotor disk valve is positioned for rotation between said manifold mounting plate and said combustor mounting plate.

3. The rotary valve multiple combustor pulse detonation engine of claim 1 further comprising a bearing system positioned on a side of said rotor disk valve facing away from said at least two detonation chambers, wherein forces from said detonation chambers on said rotor disk valve are transferred through said bearing system.

4. The rotary valve multiple combustor pulse detonation engine of claim 1 wherein said fuel manifold ends in an individual fuel port for each detonation chamber and said inlet air duct manifold ends in an individual air port for each detonation chamber and wherein said individual fuel port has an extent in one direction less than an extent of said individual air port so that when said opening of said rotor disk valve closes said individual fuel port, said individual air port remains open so that air but not fuel is introduced into said detonation chamber to create an air buffer after said detonation chamber is fueled.

5. The rotary valve multiple combustor pulse detonation engine of claim 1 wherein said fuel manifold ends in an individual fuel port for each detonation chamber and said inlet air duct manifold ends in an individual port for each detonation chamber and wherein said individual fuel port has an extent in one direction less than an extent of said individual air port, so that when said opening of said rotor disk valve opens said inlet end of said detonation chamber, said individual air port is open but said individual fuel port remains closed so that air but not fuel is introduced into said detonation chamber to purge said detonation chamber of any remaining burnt gases.

6. The rotary valve multiple combustor pulse detonation engine of claim 1 wherein said fuel source comprises a solid fueled gas generator.

7. The rotary valve multiple combustor pulse detonation engine of claim 1 wherein said fuel comprises a liquid fuel.

8. The rotary valve multiple combustor pulse detonation engine of claim 1 wherein said fuel comprises a gas fuel.

9. The rotary valve multiple combustor pulse detonation engine of claim 1 further comprising an air impingement ring at said inlet ends of said at least two detonation chambers for mixing said fuel and air.

10. The rotary valve multiple combustor pulse detonation engine of claim 1 further comprising a serrated vortex generator and a mixing mesh for mixing said fuel and air.

11. The rotary valve multiple combustor pulse detonation engine of claim 1 further comprising a pre-mixer for mixing said fuel and air before injection into said detonation chambers.

12. The rotary valve multiple combustor pulse detonation engine of claim 1 wherein said means for initiating a pulsed supersonic shock wave-triggered detonation combustion wave comprises a spark plug.

13. The rotary valve multiple combustor pulse detonation engine of claim 1 further comprising an oxidizer generator and wherein said means for initiating a pulsed supersonic shock wave-triggered detonation combustion wave comprises a separate predetonation tube which is supplied with an oxidizer from said oxidizer generator.

14. The rotary valve multiple combustor pulse detonation engine of claim 1 further comprising an oxidizer generator for supplying an oxidizer to said detonation chambers and wherein said means for initiating a pulsed supersonic shock wave-triggered detonation combustion wave comprises a separate predetonation region within said detonation chambers created by supplying said oxidizer from said oxidizer generator to said detonation chambers.

15. The rotary valve multiple combustor pulse detonation engine of claim 1 further comprising a nozzle shroud connected to said outlet ends of said at least two detonation chambers.

16. A predetonator-initiated pulse detonation engine comprising:

at least one detonation chamber, having an inlet end and an outlet end;

a fuel manifold for supplying fuel from a fuel source directly to said at least one detonation chamber at said inlet end;

an inlet air duct manifold for supplying air directly to said at least one detonation chamber at said inlet end; and

a means for initiating a pulsed supersonic shock wave-triggered detonation combustion wave for initiating detonation in said at least one detonation chamber;

wherein said means for initiating a paused supersonic shock wave-triggered detonation combustion wave comprises a predetonator.

17. The predetonator-initiated pulse detonation engine of claim 16 wherein said predetonator comprises a separate predetonation tube fueled with fuel and an oxidizer and constructed to fire into said at least one detonation chamber to initiate detonation.

18. The predetonator-initiated pulse said at least one detonation engine of claim 17 further comprising an air impingement ring at said inlet end of said detonation chamber for mixing said fuel and air.

19. The predetonator-initiated pulse detonation engine of claim 17 further comprising a serrated vortex generator and a mixing mesh for mixing said fuel and air.

20. The predetonator-initiated pulse detonation engine of claim 17 further comprising a pre-mixer for mixing said fuel and air before injection into said at least one detonation chamber.

21. The predetonator-initiated pulse detonation engine of claim 16 wherein said predetonator comprises a separate predetonation region within said at least one detonation chamber created by injecting fuel and an oxidizer into said detonation chamber.

22. The predetonator-initiated pulse detonation engine of claim 21 further comprising an air impingement ring near said inlet end of said at least one detonation chamber for mixing said fuel and air.

23. The predetonator-initiated pulse detonation engine of claim 21 further comprising a serrated vortex generator and a mixing mesh for mixing said fuel and air.

24. The predetonator-initiated pulse detonation engine of claim 21 further comprising a pre-mixer for mixing said fuel and air before injection into said at least one detonation chamber.