METHOD FOR MONITORING GAS TURBINE ENGINE TECHNICAL CONDITION Russian patent published in 2012 - IPC G01M15/14 

FIELD: aircraft engine building.

SUBSTANCE: invention can be used in electronic automatic control systems for gas turbine engines. Before the start of the engine the oil level in the engine oil container is measured, a signal “not enough oil” is formed and transmitted to the flight engineer control panel, and the oil container is filled to the required level, the air temperature is measured, oil heating in the oil container is activated and the oil temperature is measured, a signal “oil system ready for engine start” is formed and sent to the flight engineer control panel. The oil temperature is measured at the engine inlet with the running engine, and if the oil temperature at the inlet during a given period of time exceeds one quarter of a given value, a signal “high oil temperature at engine inlet” is formed and sent to the cockpit display and to the flight recorder, and the fuel-cooled oil cooler is activated. The oil temperature is measured at the outlet of the engine compressor, a signal “high oil temperature at engine compressor outlet” is formed and sent to the cockpit display and to the flight recorder. After the flight the compressor assembly is thoroughly expected, the oil temperature at the turbine pedestal is measured, a signal “high oil temperature at turbine pedestal outlet” is formed and sent to the cockpit display and to the flight recorder, and after the flight the turbine assembly is thoroughly inspected.

EFFECT: improved gas turbine engine monitoring; improved gas turbine engines reliability; improved aircraft safety.

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