Rotary valve multiple combustor pulse detonation engine
First Claim
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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.
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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.
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Citations
24 Claims
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1. A rotary valve multiple combustor pulse detonation engine comprising:
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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. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15)
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16. A predetonator-initiated pulse detonation engine comprising:
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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. - View Dependent Claims (17, 18, 19, 20, 21, 22, 23, 24)
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Specification