CPC B64D 37/00 (2013.01) [F02C 7/222 (2013.01); F02C 9/263 (2013.01); F05D 2220/323 (2013.01); F05D 2240/35 (2013.01)] | 17 Claims |
1. A fuel system for an aircraft engine, comprising:
a fuel metering unit fluidly connectable to a fuel source of the aircraft engine;
a flow divider separate from the fuel metering unit and mountable to the aircraft engine at a location remote from the fuel metering unit, the flow divider having a fuel inlet port and a fuel ecology outlet port;
a fuel line fluidly connecting the fuel metering unit to the flow divider, the fuel line including a conduit segment extending from the fuel metering unit to the flow divider, the conduit segment fluidly connected to both the fuel inlet port and the fuel ecology outlet port;
a flow restrictor between the fuel ecology outlet port and the conduit segment:
a primary and a secondary fuel manifold selectively fluidly connectable to the fuel inlet port and the fuel ecology outlet port of the flow divider;
wherein the fuel metering unit and the flow divider have a fuel supply mode in which fuel is allowed to flow in a first direction through the conduit segment of the fuel line from the fuel metering unit to the fuel inlet port of the flow divider to feed the primary and secondary fuel manifolds, and an ecology mode in which the fuel is allowed to flow in a second direction opposite to the first direction through the conduit segment of the fuel line from the fuel ecology outlet port of the flow divider to the fuel metering unit, and
wherein the flow restrictor is operable to block fuel flow in the first direction from the conduit segment to the fuel ecology outlet port of the flow divider and allow the fuel flow in the second direction from the fuel ecology outlet port to the conduit segment of the fuel line.
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