Piezo-resonance igniter and ignition method for propellant liquid rocket engine
View Patent ↗An ignition system for a rocket engine utilizes the pressure energy in a propellant flow. The propellant flow generates an oscillating pressure force in a resonance system which is then transmitted to a piezoelectric system. The electrical pulses are utilized to generate a spark in an igniter system spark gap, resulting in ignition. Since the spark energy production is driven by the resonance of the propellant flow, a fully passive auto-ignition system is provided. Once ignition occurs, the resultant backpressure in the combustion chamber “detunes” the resonance phenomena and spark production stops. Furthermore, should the engine flame out, spark production would automatically resume as the propellant valves remain open thereby providing relight capability.
1. An ignition system for a combustor comprising:
a resonance system;
a piezoelectric system driven by said resonance system; and
an igniter powered by said piezoelectric system,
said resonance system in communication with said piezoelectric system through a gas resonance tube, said gas resonance tube sealed with a force transmission diaphragm, a force transfer member in contact with said force transmission diaphragm, said force transfer member includes a force transfer rod and a force transfer platen, said force transfer platen in contact with said force transmission diaphragm and said force transfer rod in contact with a piezoelectric crystal stack.
2. The ignition system as recited in claim 1 , further comprising a working fluid inlet to said resonance system, said working fluid inlet generally opposite said gas resonance tube.
3. The ignition system as recited in claim 2 , wherein said working fluid is a gas.
4. The ignition system as recited in claim 3 , wherein said working fluid is an inert pressurant.
5. The ignition system as recited in claim 3 , wherein said working fluid is GOx.
6. The ignition system as recited in claim 2 , wherein said working fluid is an incompressible fluid.
7. The ignition system as recited in claim 1 , wherein said force transmission diaphragm includes a relief feature, a force transfer member contacts said force transmission diaphragm within said relief feature.
8. The ignition system as recited in claim 1 , wherein said force transfer platen is of a larger diameter than said force transfer rod and the force transfer diaphragm is of larger diameter than resonance tube.
9. The ignition system as recited in claim 1 , wherein said piezoelectric crystal stack is in electrical communication with said igniter.
10. The ignition system as recited in claim 1 , wherein said force transfer member includes a frustro-conical member.
11. The ignition system as recited in claim 1 , further comprising a relieved area adjacent said force transfer diaphragm adjacent an end of said gas resonance tube.
12. A combustor device comprising:
a combustor;
a working fluid system in communication with said combustor;
a resonance system in communication with said working fluid system;
a piezoelectric system driven by said resonance system;
an igniter system powered by said piezoelectric system to ignite a working fluid from said working fluid system;
a force transfer member in communication with said resonance system, said force transfer member driven by an oscillating pressure force within said resonance system;
a force transmission diaphragm in contact with said force transfer member; and
a piezoelectric crystal stack in contact with said force transfer member.
13. The combustor device as recited in claim 12 , wherein said piezoelectric system includes a force transfer member in communication with said resonance system, said force transfer member including a frustro-conical member.
14. The combustor device as recited in claim 12 , wherein said igniter system includes an electrode in direct communication with combustor.
15. The combustor device as recited in claim 12 , wherein said resonance system includes a resonance cavity in communication with said working fluid.
16. The combustor device as recited in claim 12 , wherein said resonance system includes a split leg fluidic resonator.
17. A method of igniting a combustion device comprising the steps of:
(A) communicating a working fluid to a resonance system to generate a resonance;
(B) driving a piezoelectric system with the resonance generated in said step (A), wherein said step (B) further comprises:
(a) driving a force transmission diaphragm with the resonance;
(b) driving a force transfer member in contact with the force transmission diaphragm; and
(c) driving a piezoelectric crystal stack with the force transfer member; and
(c) powering an igniter with the piezoelectric system.
18. A method as recited in claim 17 , further comprising the step of:
(D) detuning the resonance in response to ignition of the combustion device to deactivate the igniter.
19. The ignition system as recited in claim 1 , wherein said resonance system communicates an oscillating pressure into a gas resonance tube.
20. The ignition system as recited in claim 19 , wherein said force transmission diaphragm seals said gas resonance tube, said force transmission diaphragm operable to react pressure loads from said oscillating pressure in said gas resonance tube.
21. The combustor device as recited in claim 12 , wherein said combustor is a thrust chamber assembly combustor.
22. The combustor device as recited in claim 12 , wherein said resonance system communicates an oscillating pressure into a gas resonance tube.
23. The combustor device as recited in claim 22 , wherein said force transmission diaphragm seals said gas resonance tube, said force transmission diaphragm operable to react pressure loads from said oscillating pressure in said gas resonance tube.
24. The ignition system as recited in claim 1 , wherein said resonance system is in communication with said piezoelectric system through a gas resonance tube, an oscillation pressure caused by a resonant flow interaction between a jet flow into said gas resonance tube.