A Study on the Ignition System of a Pilot Flame in a Cannon-type-combustor of a Turbo-engine

We studied a stable pilot flame system for a cannon type combustor of turbo-engines by adding both a frontchamber and a pilot flame chamber with an electric ignition system to the conventional two-stage system with two-stage combustion domains: a primary zone and a secondary zone. The electric ignition period was about 1 second with 2760V(theoretical) generated by Kochcroft-Welton circuit, and the fuel was butane gas. The inlet was 25m/sec and the pressure was about 400Pascal at the inlet of combustor.We set two cases for the outlet configuration: a converging nozzle and a turbine. The outlet temperature was 280C at the outlet velocity of 25m/sec, and the temperature was 230C at the outlet velocity of 12m/sec. A sufficiently large rotational speed and torque was obtained to rotate the compressor and fan of the turbine. Weanalyzed the ignition mechanism by solving two dimensional compressible Navier-Stokes equations and found that the role of the front chamberwas to maintain the pilot flame after the ignition shock. We confirmed experimentally that this system can ignite and preserve a stable pilot flame with quite high probability.