| CPC F02C 9/40 (2013.01) [F02C 7/222 (2013.01); F02C 7/232 (2013.01); F23D 2209/30 (2013.01); F23R 3/36 (2013.01)] | 6 Claims |
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1. A fuel system of an aircraft engine, comprising:
a combustor;
a liquid fuel circuit selectively fluidly connected to the combustor via a liquid fuel manifold;
a gaseous fuel circuit selectively fluidly connected to the combustor via a gaseous fuel manifold;
an inert gas source selectively fluidly connected to the gaseous fuel manifold; and
a controller configured to, during a shutdown of the aircraft engine, cause inert gas from the inert gas source to be issued to the gaseous fuel manifold while gaseous fuel is issued to the gaseous fuel manifold to cause mixing of the inert gas with the gaseous fuel;
wherein:
the gaseous fuel manifold fluidly communicates a gaseous fuel supply with at least one dual fuel nozzle downstream of the gaseous fuel manifold;
the fuel system further comprises a purge gas circuit in fluid communication with the inert gas source and the gaseous fuel manifold such that the gaseous fuel circuit and the purge gas circuit share a common outlet of the gaseous fuel manifold;
the liquid fuel circuit fluidly communicates a liquid fuel supply with the at least one dual fuel nozzle downstream of the liquid fuel supply;
the purge gas circuit is in fluid communication with the liquid fuel manifold such that the liquid fuel circuit and the purge gas circuit share a common outlet of the liquid fuel manifold; and
the purge gas circuit includes at least one three-way valve configured to issue the inert gas to the gaseous fuel manifold and the liquid fuel manifold simultaneously.
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