Abstract: A gas turbine engine includes 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 and a bypass passage separate from the core passage, a low-speed shaft coupled to and configured to rotate the plurality of fan blades, and a sensor assembly coupled to the gas turbine engine and configured to detect torsional vibration in the low-speed shaft. The sensor assembly includes a plurality of dynamic pressure sensors in the airflow passage. The plurality of dynamic pressure sensors detect a dynamic pressure of the airflow passage that is indicative of the torsional vibration in the low-speed shaft. A damping system is configured to dampen the torsional vibration in the low-speed shaft based on a correlation of a measured torsional vibration and an experimental torsional vibration.

Abstract: A gas turbine engine includes 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 and a bypass passage separate from the core passage, a low-speed shaft coupled to and configured to rotate the plurality of fan blades, and a sensor assembly coupled to the gas turbine engine and configured to detect torsional vibration in the low-speed shaft. The sensor assembly includes a plurality of dynamic pressure sensors in the airflow passage. The plurality of dynamic pressure sensors detect a dynamic pressure of the airflow passage that is indicative of the torsional vibration in the low-speed shaft. A damping system is configured to dampen the torsional vibration in the low-speed shaft based on a correlation of a measured torsional vibration and an experimental torsional vibration.

Abstract: Systems and techniques that facilitate predictive core rub diagnostics are provided. A sensor component can collect real-time operation parameters of a gas turbine engine. An analysis component can statistically combine first values, second values, and third values to yield a rub indicator for the engine. The first values can be based on a first comparison of fundamental mode placements of the engine, derived from the real-time operation parameters, and baseline fundamental mode placements. The second values can be based on a second comparison of a vibration spectrum of the engine, derived from the real-time operation parameters, and a baseline vibration spectrum. The third values can be based on a third comparison of the real-time operation parameters of the engine and baseline operation parameters. A classification component can generate a rub classification report indicating presence of rubbing in the engine, based on the rub indicator.

Abstract: Systems and techniques that facilitate predictive core rub diagnostics are provided. A sensor component can collect real-time operation parameters of a gas turbine engine. An analysis component can statistically combine first values, second values, and third values to yield a rub indicator for the engine. The first values can be based on a first comparison of fundamental mode placements of the engine, derived from the real-time operation parameters, and baseline fundamental mode placements. The second values can be based on a second comparison of a vibration spectrum of the engine, derived from the real-time operation parameters, and a baseline vibration spectrum. The third values can be based on a third comparison of the real-time operation parameters of the engine and baseline operation parameters. A classification component can generate a rub classification report indicating presence of rubbing in the engine, based on the rub indicator.