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

Claim 0:
1. A system for monitoring components of an engine of an aircraft comprising:
a gas compressor turbine of the engine;
a power turbine of the engine;
a turboshaft gearbox;
an accessory gearbox in the turboshaft gearbox and configured to be driven by the gas compressor turbine;
a power gearbox in the turboshaft gearbox and configured to be driven by the power turbine; and
a sensor positioned on the turboshaft gearbox and configured to detect vibration signals related to components of both the gas compressor turbine and the power turbine;
wherein the sensor is configured to determine, based on the vibration signals, a condition indicator representative of a condition of a monitored component of the gas compressor turbine and a condition indicator representative of a condition of a monitored component of the power turbine.