System and method for variable geometry mechanism configuration

A system for configuring at least one variable geometry mechanism (VGM) of an aircraft engine, the system comprising:

• at least one processing unit;
• and
• a non-transitory computer readable medium having stored thereon program code executable by the at least one processing unit for:
• obtaining pass-off testing data for the aircraft engine during pass-off testing of the aircraft engine, the pass-off testing data indicative of an actual value of at least one operating parameter of the aircraft engine;
• determining, based on the pass-off testing data, at least one trim value to be used to adjust a setting of the at least one VGM to bring the actual value of the at least one operating parameter towards a target value, a running line of the aircraft engine being substantially constant when the actual value of the at least one operating parameter is at the target value, wherein the running line is defined as a function of a first parameter and a second parameter of the aircraft engine, the determining comprising:
• obtaining a virtual engine model for simulating a behaviour of the aircraft engine:
• running the virtual engine model to determine a position of the at least one VGM at which the actual value of the at least one operating parameter is brought towards the target value, the running the virtual engine model comprising:
• aligning the virtual engine model with the pass-off testing data to obtain an aligned model;
• running the aligned model to simulate the behaviour of the aircraft engine at a target value of the first parameter;
• determining a first position of the at least one VGM at which a target value of the second parameter is achieved;
• determining a current value of a third parameter of the aircraft engine with the at least one VGM in the first position;
• running the aligned model to simulate the behaviour of the aircraft engine at the current value of the third parameter to determine a second position of the at least one VGM;
• and
• determining the at least one trim value by subtracting the first position from the second position;
• and
• determining the at least one trim value based on the position of the at least one VGM as determined;
• and
• adjusting, during the pass-off testing of the aircraft engine, the setting of the at least one VGM using the at least one trim value.