Patent ID: 11885711
Assignee: GPMS INTERNATIONAL, INC.
Field: Measurement (Instruments)
Classification: CPC G | IPC G

Claim 12:
13. A method for monitoring components of a turbine engine of an aircraft comprising:
mounting a sensor on a turboshaft gearbox of the turbine engine such that the sensor is positioned to acquire vibration data related to a gas compressor turbine and a power turbine of the turbine engine;
acquiring, at the sensor, vibration data related to the gas compressor turbine and the power turbine;
determining in the sensor based on the vibration data a tachometer value for a monitored component of the gas compressor turbine and a tachometer value for a monitored component of the power turbine;
determining in the sensor a condition indicator for the monitored component of the gas compressor turbine based on the vibration data and the tachometer value for the monitored component of the gas compressor turbine; and
determining in the sensor a condition indicator for the monitored component of the power turbine of the power turbine based on the vibration data and the tachometer value for the monitored component of the power turbine.