Patent ID: 6483022
Filing Date: 2002-11-19
Classification: H01B,H01R

Abstract:
A pressurized ignition lead assembly for an aircraft engine, said ignition lead assembly comprising:an ignition cable; a conduit extending circumferentially around said ignition cable and comprising an air-cooled portion and a non-air-cooled portion, said conduit further comprising an opening extending between an exterior and an interior surface of said conduit for supplying cooling air to said conduit air-cooled portion; a seal sub-assembly between said ignition lead assembly air-cooled portion and said ignition lead assembly non-air-cooled portion, said seal sub-assembly comprising a housing and a seal therein, said seal sub-assembly configured to prevent a loss of air pressure from said pressurized ignition lead assembly; and an engine coupling attached to said ignition lead assembly non-air cooled portion for attaching said ignition cable to the gas turbine engine, said engine coupling comprising a seal configured to prevent pressure decreases of air from said engine coupling.