SYSTEMS AND METHODS FOR PURGING A FUEL MANIFOLD OF A GAS TURBINE ENGINE

Fuel systems of gas turbine engines (14) of aircraft, and associated methods (500, 700) can permit reverse purging of one or more fuel manifolds of a gas turbine engine (14) to prevent coking in some modes of operation. A fuel system includes first and second fuel manifolds (34A, 34B) fluidly connectable to a combustor (20) of the gas turbine engine (14). A valve (52) is operatively disposed between the second fuel manifold (34B) and a fuel supply line (58) for controlling fuel supply to the second fuel manifold (34B). A reservoir (64) includes a movable piston (66) disposed therein and dividing the reservoir (64) into a first chamber (64A) and a second chamber (64B). The first chamber (64A) is fluidly connectable to the fuel supply line (58) or to a fuel purge line (68) via the valve (52). The second chamber (64B) is in fluid communication with the second fuel manifold (34B) to receive residual fuel from the second fuel manifold (34B).