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 torchfromburning ofgaseousoxygenandliquidkerosenewasdesignedandtested.Theoxygen isheatedfor0, 1sin 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 e ow rates. This opens new possibilities to create a compact and reliable ignition system for restarting rocket engines. Nomenclature P m f; P mo = mass e ow rate of kerosene and oxygen, respectively, kg/s O=F = P mo= P m f , mixture ratio pc = chamber pressure, bar p f; po = inlet pressure of kerosene and oxygen, respectively, bar TB = temperature of the igniter body, K TR = temperature of the outer surface of resonator, K TT = temperature of the torch, K t = time, s t f = moment when the fuel valve is turned on, s tig = moment of ignition, s to = moment when the oxygen valve is turned on, s toff = moment when the fuel valve is turned off, s 1tig = time delay of ignition, s 1to = igniter preparation interval, s 1top = igniter operation interval, s