ONBOARD MONITORING SYSTEM OF AIRCRAFT ENGINE AT LIMITED ROTATIONAL SPEED, FUEL PARAMETERS AND THRUST Russian patent published in 2005 - IPC

FIELD: aircraft instrumentation engineering; monitoring of gas-turbine engines.

SUBSTANCE: proposed onboard monitoring system ensures check of engine in standard, off-standard and augmented power rating modes. Monitoring is based on use of information received from aircraft engine sensors and transmitted to inputs of multiplexing unit and from outputs of this unit to onboard computer. Information received from sensors of very important parameters of aircraft engine is fed directly to input of command unit. Computational algorithms and information received from sensors pertaining to dangerous parameters of aircraft engine, viz.: rotational speed of high-pressure compressor rotor, consumption and pressure of fuel and thrust are compared with limiting and dangerous magnitudes; in case signals are beyond these magnitudes, limiting and dangerous commands are formed and are transmitted to onboard computer and to emergency information system of aircraft for recording and for warning the crew. Actual operating hours and remaining service life of aircraft engine are determined in onboard computer with the commands taken into account and are transmitted to onboard information recording and indication system.

EFFECT: enhanced efficiency of monitoring the engine working at increased thrust.

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