Patent ID: 11898496
Assignee: HAMILTON SUNDSTRAND CORPORATION
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 0:
1. A fuel system of an aircraft engine, comprising:
a boost pump having an input and an output;
one or more selector valves;
a first component pump having an input fluidly coupled to the output of the boost pump and an output of the first component pump is configured to direct fuel to a first component via the one or more selector valves; and
a second component pump having an input that is selectively coupled to either the input or the output of the boost pump by the one or more selector valves, and an output of the second component pump is fluidly coupled to a second component and selectively coupled to the first component by the one or more selector valves, and
a plurality of flowpaths, including:
a first flowpath extending between the output of the boost pump and the input of the first component pump;
a second flowpath extending between the output of the first component pump and the first component via the one or more selector valves;
a third flowpath extending between the input of the boost pump and the input of the second component pump via the one or more selector valves;
a fourth flowpath extending between the output of the second component pump and the second component;
a fifth flowpath extending between the fourth flowpath and the first component via the one or more selector valves; and
a sixth flowpath extending from the first flowpath, between the output of the boost pump and the first component pump, to the third flowpath via the one or more selector valves.