Patent US5345758A successfully refreshed from Google Patents.
US5345758A
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Rotary valve multiple combustor pulse detonation engine
Assignee: SHOCKSystem Inc
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Filing: 1993-04-14
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Granted: 1994-09-13
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Expires: 2013-04-14
Abstract
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.
Inventors
- 👤 Thomas R. Bussing
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-25 23:21
CPC Classifications
F; F02; F02K; F02K9/00; F02K9/97; F02K9/974; B; B01; B01J; B01J3/00; B01J3/06; B01J3/08; B05; B05B; B05B7/00; B05B7/0006; C; C23; C23C; C23C4/00; C23C4/12; C23C4/126; F01; F01D; F01D5/00; F01D5/12; F01D5/28; F01D5/288; F02K7/00; F02K7/02; F02K7/06; F02K7/075; F02K9/972
Claims Analysis
Total Claims: 26
Claim 1
Independent Claim
219 words
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.
Claim 2
Dependent Claim
219 words
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.
Claim 3
Dependent Claim
60 words
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.
Claim 4
Dependent Claim
51 words
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.
Claim 5
Dependent Claim
106 words
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.
Claim 6
Dependent Claim
114 words
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.
Claim 7
Dependent Claim
21 words
The rotary valve multiple combustor pulse detonation engine of claim 1 wherein said fuel source comprises a solid fueled gas generator.
Claim 8
Dependent Claim
18 words
The rotary valve multiple combustor pulse detonation engine of claim 1 wherein said fuel comprises a liquid fuel.
Claim 9
Dependent Claim
18 words
The rotary valve multiple combustor pulse detonation engine of claim 1 wherein said fuel comprises a gas fuel.
Claim 10
Dependent Claim
34 words
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.
Claim 11
Dependent Claim
27 words
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.
Claim 12
Dependent Claim
27 words
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.
Claim 13
Dependent Claim
28 words
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.
Claim 14
Dependent Claim
45 words
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.
Claim 15
Dependent Claim
60 words
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.
Claim 16
Dependent Claim
28 words
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.
Claim 17
Dependent Claim
100 words
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.
Claim 18
Dependent Claim
100 words
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.
Claim 19
Dependent Claim
36 words
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.
Claim 20
Dependent Claim
32 words
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.
Claim 21
Dependent Claim
24 words
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.
Claim 22
Dependent Claim
27 words
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.
Claim 23
Dependent Claim
34 words
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.
Claim 24
Dependent Claim
31 words
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.
Claim 25
Dependent Claim
24 words
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.
Claim 26
Dependent Claim
27 words
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.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1997-09-12 | 1998-03-14 | 1998-09-13 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 2001-09-12 | 2002-03-14 | 2002-09-13 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2005-09-12 | 2006-03-14 | 2006-09-13 | $7700.00 | Window Closed / Lapsed |