Electronically driven lubrication system on gas turbine engines

An electronically driven lubrication system comprising:

• an electric lubrication pump;
• at least one bearing for a gas turbine engine component;
• an oil cooler fluidly coupled with the electric lubrication pump;
• lubrication oil fluidly coupled with the electric lubrication pump, at least one bearing and oil cooler;
• at least one sensor in operative communication with the lubrication oil;
• a controller comprising a processor in operative communication with the at least one sensor, the electric lubrication pump, the at least one bearing and the oil cooler;
• and
• the processor configured to provide processor outputs to the electric lubrication pump responsive to data collected from the at least one sensor, wherein the processor employs an operational configuration for the electronically driven lubrication system;
• a tangible, non-transitory memory configured to communicate with said processor, the tangible, non-transitory memory having instructions stored therein that, in response to execution by the processor, cause the processor to perform operations comprising:
• receiving, by the processor, sensor data for determination of electronically driven lubrication system operational parameters;
• receiving, by the processor, sensor data for determination of gas turbine engine operational parameters;
• receiving, by the processor, sensor data for determination of aircraft operational parameters;
• configuring, by the processor, the operational configuration for the electronically driven lubrication system;
• adjusting, by the processor, the electric lubrication pump speed;
• adjusting, by the processor, the lubrication oil flow path;
• and
• configuring, by the processor, the electric lubrication pump to function as a deprime valve in order to shutdown or reduce flow of lubrication oil responsive to an auxiliary power unit winding down.