Variable pitch stator blade control

Abstract

This presentation relates to a computer-implemented method comprising: determining a target pitch angle value for a blade (40b, 50b) of a stator section of a compressor stage in an aircraft propulsion system, based on a parameter value (P) representative of wear in the aircraft propulsion system; and generating a control signal (S) configured to control a blade (400) piloting device (400) such that the piloting device (400) adjusts a blade (40b, 50b) pitch angle (α) to the determined target pitch angle value. Figure 4 for the abstract