Piezo-resonance igniter and ignition method for propellant liquid rocket engine
US7565795B1 · kind B1 · utility
Assignee
Inventors
Key dates
| Filing date | Jan 17, 2006 |
| Grant date | Jul 28, 2009 |
| Priority date | — |
| Expiry date | Jun 9, 2027 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02P3/12
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
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.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.