Post-combustion fuel ignition system for gas turbine engine of military aircraft, has spring displaced relative to pipe due to passage of fuel in pipe during its functioning and covered with material having less friction co-efficient

摘要

The system has a spring (30) placed in a bore of a fuel supply pipe (23) and housed in a tubular body (19) of an injector (17), where the spring is displaced with respect to the pipe under the action of passage of fuel in the pipe during the functioning of the spring. The spring is covered with material having less friction co-efficient, and the pipe extends along the tubular body of the injector. The pipe injects a fuel spray into a combustion chamber.