Development of a Resonance Igniter for GO/Kerosene Ignition

Abstract

A resonance ignition system is attractive for rocket engines because of the igniter's simplicity and the possibility of multiple ignitions without additional mechanical complexities. In this work a resonance igniter to produce a torch from burning of gaseous oxygen and liquid kerosene was designed and tested. The oxygen is heated for 0, 1 s in the acoustic resonator cavity, and the ignition occurs instantaneously on kerosene injection. The preliminary tests under ambient conditions demonstrated the igniter's ability to ignite GO 2 /kerosene mixtures over a wide range of pressures and mass ow rates. This opens new possibilities to create a compact and reliable ignition system for restarting rocket engines. NomenclatureP m f ; P m o = mass ow rate of kerosene and oxygen, respectively, kg/s O=F = P m o = P m f , mixture ratio p c = chamber pressure, bar p f ; p o = inlet pressure of kerosene and oxygen, respectively, bar T B = temperature of the igniter body, K T R = temperature of the outer surface of resonator, K T T = temperature of the torch, K t = time, s t f = moment when the fuel valve is turned on, s t ig = moment of ignition, s t o = moment when the oxygen valve is turned on, s t off = moment when the fuel valve is turned off, s 1t ig = time delay of ignition, s 1t o = igniter preparation interval, s 1t op = igniter operation interval, s