Gas turbine engine having a sensor assembly to detect torsional vibration

A gas turbine engine having a sensor assembly configured to detect torsional vibration, the gas turbine engine comprising:

• a fan section having a plurality of fan blades, the fan section configured to generate an airflow through the gas turbine engine;
• an airflow passage having:
• a core passage configured to guide a first portion of the airflow from an inlet to an exhaust nozzle;
• and
• a bypass passage separate from the core passage and configured to guide a second portion of the airflow to bypass the core passage;
• a low-speed shaft coupled to and configured to rotate the plurality of fan blades;
• a sensor assembly comprising a plurality of dynamic pressure sensors in the airflow passage, the plurality of dynamic pressure sensors detecting a dynamic pressure of the airflow passage that is indicative of torsional vibration in the low-speed shaft, a processor configured to determine a measured torsional vibration from the detected dynamic pressure;
• and
• a damping system configured to dampen the torsional vibration in the low-speed shaft based on a correlation of the measured torsional vibration and an experimental torsional vibration.