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AssigneeRolls-Royce Deutschland Ltd & Co KG
InventorsThomas JÄGER, Markus BLUMRICH
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A fuel system for a gas turbine engine, includes a fuel line connecting a fuel tank to s feed pump and a fuel filter. The fuel filter is downstream of the feed pump and connected via the fuel line to a pressure side of the feed pump and a combustion chamber. A return line branches from the combustion chamber toward a return reservoir. A suction charging line connects the pressure side of the feed pump to a suction side of the feed pump. The return reservoir is operatively connected to the suction charging line via an emptying unit for conducting fuel from the return reservoir into the suction charging line. The suction charging line branches from the fuel filter toward the suction side of the feed pump and fuel can be introduced from an interior of a filter housing of the fuel filter into the suction charging line.
A fuel system for a gas turbine engine, in particular for an aircraft gas turbine, comprising a fuel line, which connects a fuel tank to at least one feed pump, to a fuel filter arranged downstream of the feed pump and connected to a pressure side of the feed pump, and to a combustion chamber connected to the fuel line downstream of the fuel filter, and comprising a return line, which branches off from the combustion chamber in the direction of a return reservoir, and comprising a suction charging line, which connects the pressure side of the feed pump to a suction side of the feed pump, wherein the return reservoir is operatively connected to the suction charging line via an emptying unit, wherein the emptying unit is configured to conduct fuel from the return reservoir into the suction charging line, wherein the suction charging line branches off from the fuel filter in the direction of the suction side of the feed pump and fuel can be introduced from an interior of a filter housing of the fuel filter into the suction charging line.
Dependencies are inferred from the claim text.