CPC F02C 7/30 (2013.01) [F02C 6/00 (2013.01); F02C 6/16 (2013.01); F02C 7/222 (2013.01); F02C 7/228 (2013.01); F02C 7/232 (2013.01); F02C 7/236 (2013.01); F02C 9/32 (2013.01); F02C 9/42 (2013.01)] | 8 Claims |
1. A fuel system of a gas turbine engine, the fuel system comprising:
a pressurized gas source;
a first fuel manifold fluidly connectable to a combustor of the gas turbine engine;
a second fuel manifold fluidly connectable to the combustor; and
a flow divider valve actuatable between a first configuration and a second configuration, wherein:
in the first configuration, the flow divider valve is configured to supply fuel to the first and second fuel manifolds; and
in the second configuration, the flow divider valve is configured to:
supply fuel to the first fuel manifold,
stop supplying fuel to the second fuel manifold, and
permit pressurized gas to be supplied from the pressurized gas source to the second fuel manifold to flush fuel in the second fuel manifold into the combustor.
|