Patent ID: 9133772
Filing Date: 2015-09-15
Classification: F02C,F04B,F05D

Abstract:
1. An aircraft engine fuel system, comprising: a pump, including a pump inlet and a pump outlet, from which pressurized output is produced; a valve comprising a valve case defining an interior and a piston translatable within the interior, the valve being disposed downstream from the pump outlet and the valve case forming a valve inlet to receive a predefined portion of the output, a valve outlet to redirect a predefined portion of the output toward an engine and a bypass opening axially interposed between the valve inlet and the valve outlet; a bypass conduit, which is fluidly coupled at an inlet thereof to the bypass opening of the valve and at an outlet thereof to the pump inlet, by which a remaining portion of the output is able to be re-circulated to the pump inlet; a sensor coupled to a driveshaft of the piston of the valve and configured to ascertain axial translations of the piston from axial translations of the driveshaft and to issue a signal reflective of the axial translations of the piston at engine startup and maximum fuel flow conditions; and a controller, operably coupled to the pump and the sensor, which is receptive of the signal and which: compares the axial translations of the piston at the engine startup and maximum fuel flow conditions to determine whether changes in the axial translations of the piston are associated with decreased pump capacity due to wear, and controls the pump to modify performance models of the pump and engine to modify the output pressure in accordance with a determination that the changes in the axial translations of the piston are associated with the decreased pump capacity due to wear.