US Patent 8375697 Electrolytic igniter for rocket engines using liquid propellants

The electrolytic ignitor comprises an injector constituting a first electrode and including a fuel injector device, an oxidizer injector device, and an electrolyte injector device. A second electrode electrically insulated from the injector extends downstream beyond the injector. An electrolyte distribution channel for delivering electrolyte in the form of free jets through the electrolyte injector device comprises at least one injection hole in the vicinity of the fuel injector device and the oxidizer injector device. An electrical power supply circuit is adapted to raise the second electrode to a potential in the range 50 V to 1000 V relative to the potential of the first electrode. The electrolyte injected through the injection hole is capable of causing ignition of a gaseous mixture in a combustion chamber of an ignitor torch suitable for incorporating in a main injector of a rocket engine.