Energy efficient pump system

1. A fuel system for a gas turbine engine that includes a combustor section and an actuator, the fuel system comprising:

a fuel source;

a combustor system including a combustor pump that is fluidly connected to the fuel source and to the combustor section, the combustor pump being mechanically connected to and powered by a first electric motor;

an actuation system including an actuation pump that is fluidly connected to the fuel source and to the actuator, the actuation pump being mechanically connected to and powered by a first force source;

a fail selector that is fluidly connected to the combustor pump, the actuator pump, the combustor section, and the actuator, the fail selector having three settings comprising:

a first setting that allows no flow through the fail selector;

a second setting that allows flow from the combustor pump to both the combustor section and the actuator through the fail selector; and

a third setting that allows flow from the actuator pump to both the combustor section and the actuator through the fail selector;

an afterburner system including an afterburner pump that is fluidly connected to the fuel source and to an afterburner, the afterburner pump being mechanically connected to and powered by a turbomachine or a third electric motor; and

a pump selector that is fluidly connected to the afterburner system and is fluidly connected between the fuel source and the combustor system, the pump selector having two settings comprising:

a first setting that allows flow from the fuel source to the combustor section; and

a second setting that allows flow from the afterburner system to the combustor system.

2. The fuel system of claim 1 , wherein the first force source is a gearbox.

3. The fuel system of claim 1 , wherein the first force source is a second electric motor.

4. The fuel system of claim 1 , wherein the second force source is a turbomachine.

5. The fuel system of claim 1 , wherein the second force source is a third electric motor.

6. The gas turbine engine of claim 5 , and further comprising:

a boost pump fluidly connected between the fuel source and the combustor and actuator pumps;

wherein the boost pump is mechanically connected to and powered by the first force source.

7. The fuel system of claim 1 , and further comprising:

a boost pump fluidly connected between the fuel source and the combustor and actuator pumps.

8. A gas turbine engine including the fuel system of claim 1 , the gas turbine engine further comprising:

a compressor upstream of the combustor section;

a turbine downstream of the combustor section; and

a shaft that couples the turbine to the compressor.

9. The gas turbine engine of claim 8 , wherein the first force source is a gearbox that is connected to the shaft.

10. A method of operating a fuel system for a gas turbine engine that includes a combustor section, an afterburner, and an actuator, the method comprising:

powering a combustor pump with an electric motor;

flowing fuel from a fuel source to the combustor section using the combustor pump;

powering an actuator pump with a gearbox or an electric motor;

flowing fuel from the fuel source to the actuator using the actuator pump;

powering an afterburner pump with a turbomachine;

flowing fuel from the fuel source to the afterburner using the afterburner pump;

flowing fuel from the fuel source to the combustor pump using the afterburner pump; and

flowing fuel from the fuel source to both the combustor section and the actuator using the combustor pump after a failure of the actuator pump.