Launcher/Vast Igniter Development

Igniter Parameters 

I was approached by Launcher (now Vast) to develop an ignition system for the E-2 Rocket engine, a 10-ton thrust oxygen-rich staged combustion rocket engine. This igniter would light the oxygen-rich preburner. I was given the requirements of having it operate up to 50 bar of chamber pressure, be reusable, regeneratively cooled to allow it to run up to 5 seconds continuously with no damage, use RP-1 and gOX and be made of Inconel 718 or CuCrZr. Using a similar sizing script as the previous igniters I've designed, adding in a very primitive regen channel analysis portion I produced the following igniter: