| CPC F23R 3/283 (2013.01) [F02C 7/16 (2013.01); F02C 7/22 (2013.01)] | 13 Claims |
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1. A fuel system for a gas turbine engine comprises:
a manifold assembly comprising:
an assembly inlet;
an assembly outlet;
a plurality of fuel injectors, each of the plurality of fuel injectors further comprising:
a strut extending radially inward from an outer end toward a center axis of the gas turbine engine;
a nozzle head connected to the strut opposite the outer end of the strut;
a first valve seat in the strut and closer to the nozzle head than to the outer end of the strut, or the first valve seat is in the nozzle head;
a second valve seat in the strut and closer to the nozzle head than to the outer end of the strut, or the second valve seat is in the nozzle head;
a return passage extending from the outer end of the strut to the first valve seat;
a supply passage extending from the outer end of the strut to the second valve seat;
a nozzle exit formed on the nozzle head and fluidically connected to the second valve seat; and
a valve head between the first valve seat and the second valve seat,
wherein in a first position the valve head is against the first valve seat and fluidically opens the nozzle exit to the supply passage and fluidically closing the return passage to both the nozzle exit and the supply passage when the gas turbine engine is on, and
wherein in a second position the valve head is against the second valve seat and fluidically closes the nozzle exit to both the supply passage and the return passage and fluidically opens the return passage to the supply passage when the gas turbine engine is off; and
at least one fuel manifold fluidically connecting each fuel injector of the plurality of fuel injectors to the assembly inlet and to the assembly outlet;
a fuel return line fluidically connected to the assembly outlet; and
a fuel circulator pump comprising:
a pump outlet fluidically connected to the assembly inlet.
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