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

Claim 3:
4. A system for monitoring components of a turboshaft, turboprop, or twin spindle turbofan engine of an aircraft comprising:
a gas compressor turbine of the engine;
a power turbine of the engine;
an accessory gearbox configured to be driven by the gas compressor turbine;
a power gearbox configured to be driven by the power turbine;
a sensor positioned on a turboshaft gearbox and configured to detect vibration signals from components of both the gas compressor turbine and the power turbine; and
an on-board control unit in communication with the sensor and configured to receive inputs from a plurality of instruments on the aircraft,
wherein the on-board control unit is configured to determine a current regime of the aircraft based on the inputs and wherein, based on the current regime, the on-board control unit is configured to execute a script for directing the sensor to acquire vibration data for a specified time at a sample rate representative of the vibration signals.