| CPC F02C 7/222 (2013.01) [F02C 7/232 (2013.01); F05D 2220/323 (2013.01); F05D 2260/60 (2013.01)] | 16 Claims |
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1. A fuel system of an aircraft engine, comprising:
a fuel manifold extending around a central axis, the fuel manifold having a first manifold inlet and a second manifold inlet;
fuel nozzles fluidly connected to the fuel manifold and circumferentially distributed around the central axis, the fuel nozzles located downstream of the first manifold inlet and of the second manifold inlet relative to a flow of fuel from a fuel source to the fuel nozzles;
a flow divider valve upstream of the first manifold inlet and of the second manifold inlet of the fuel manifold and upstream of all of the fuel nozzles being fluidly connected to the fuel manifold;
a transfer tube assembly downstream of the flow divider valve and upstream of the first manifold inlet and of the second manifold inlet, the transfer tube assembly located upstream of all of the fuel nozzles being fluidly connected to the fuel manifold, the transfer tube assembly having a first tube slidably engaged to the fuel manifold and fluidly connected to the first manifold inlet, and a second tube slidably engaged to the fuel manifold and fluidly connected to the second manifold inlet; and
an adaptor located downstream of the flow divider valve and upstream of both of the transfer tube assembly and the fuel manifold, the adaptor having:
a body slidably engaged by the first tube and by the second tube,
a first member defining a first fuel conduit fluidly connected to the first manifold inlet via the first tube, and
a second member defining a second fuel conduit fluidly connected to the second manifold inlet via the second tube.
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