Patent ID: 9657643
Date: 2017-05-23
CPC Classifications: F02C

Claim:
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: 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: