| CPC F02C 7/222 (2013.01) [F05D 2260/31 (2013.01); F23R 3/60 (2013.01)] | 7 Claims |
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1. A fuel system of an aircraft engine having a centerline axis, the fuel system comprising:
a flow divider valve mounted at a first mounting point on the aircraft engine;
a fuel manifold having a nozzle-input interface, the fuel manifold mounted at a second mounting point on the aircraft engine, the first and second mounting points spaced axially relative to the centerline axis;
a manifold adapter interchangeably connectable between the flow divider valve and the fuel manifold, the manifold adapter disposed upstream of the fuel manifold relative to a fuel flow from the flow divider valve to the fuel manifold, the manifold adapter held in position fixedly relative to the flow divider yet movably relative to the fuel manifold,
the manifold adapter comprising:
a body having a body-input interface and a body-output interface, the body mounted at a third mounting point on the aircraft engine, the third mounting point separate and axially spaced from the first and second mounting points;
the body-input interface rigidly connectable via a rigid supply line to the flow divider valve so as to locate the body-output interface in axial alignment with the nozzle-input interface of the fuel manifold, the nozzle-input interface having an axial component parallel to the centerline axis of the aircraft engine,
the body-output interface slidably engaged along a direction parallel to the centerline axis with an upstream-tube end of a linear transfer tube having a downstream-tube end slidably engaged with the nozzle-input interface, the linear transfer tube extending parallel to the centerline axis, the body-output interface and the nozzle-input interface slidably engaged via the linear transfer tube and thermally decoupled via the linear transfer tube.
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