An aircraft fuel system includes a first pump system that is mechanically driven and in selective fluid communication with a fuel tank and a fuel nozzle of an engine. The first pump system is configured to pump fuel to the fuel nozzles in a high flow rate condition and to be starved or nearly starved of fuel in a low flow rate condition. The aircraft fuel system includes a second pump system including an electric motor. The second pump system is in fluid communication with the fuel tank and the fuel nozzle to pump fuel from the fuel tank to the fuel nozzles. The second pump system is driven by the electric motor and is configured to pump flow in both the high flow rate condition and the low flow rate condition.
AIRCRAFT FUEL PUMP SYSTEMS
2018-02-22
Patent
Electronic Resource
English