VARIABLE GUIDE VANE ASSEMBLY AND CONTROL SYSTEM THEREOF

A method of operating a variable guide vane assembly (40) of an aircraft engine (10), the variable guide vane assembly (40) including guide vanes (42) rotatable about respective spanwise axes (S1) and circumferentially distributed about a central axis (11), the method comprising: obtaining a target exit flow angle defined between a direction of a flow exiting the guide vanes (42) and the central axis (11); predicting an exit flow angle (T2; T2') as a function of at least a geometric angle (T1), the exit flow angle (T2; T2') defined between the direction of the flow (F1; F1') exiting the guide vanes (42) and the central axis (11), the geometric angle (T1) defined between the guide vanes (42) and the central axis (11); and when a difference between the exit flow angle (T2; T2') and the target exit flow angle is above a threshold, modulating the guide vanes (42) to modify the geometric angle (T1) until the difference between the exit flow angle (T2; T2') and the target exit flow angle is at or below the threshold.