Patent ID: 6199370
Filing Date: 2001-03-13
Classification: F02K

Abstract:
An acoustic igniter for igniting a mixture of propellents in the combustion chamber of a liquid propellent rocket engine, the igniter comprising a cylindrical precombustion chamber having a cylindrical wall and first and second end walls, a propellent injection nozzle opening out into the precombustion chamber through the first end wall via an orifice of minimum diameter d.sub.n, a fuel injector disposed inside said propellant injection nozzle on the axis thereof, at least one outlet orifice of minimum diameter d.sub.f, formed through the cylindrical wall, and an acoustic resonator defining a cavity opening out into the precombustion chamber opposite the propellant injection nozzle through the second end wall via an opening of diameter d.sub.r,the igniter being characterized in that the acoustic resonator is surrounded by a housing which defines an auxiliary chamber around the acoustic resonator, the auxiliary chamber being closed with the inside thereof being in communication only with the precombustion chamber via at least one duct.