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

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

SUBSTANCE: proposed monitoring system makes it possible to check engines working in standard, off-standard and augmented power rating modes. Monitoring is based on use of information received from sensors of aircraft engine parameters and transmitted to inputs of multiplexing unit and from output of this unit to onboard computer. Information received from sensors of very important parameters of aircraft engine is fed directly to command unit input. Magnitudes of very important parameters of aircraft engine, viz.: rotational speed on high-pressure compressor, turbine exhaust gas temperature and consumption and pressure of fuel are compared in onboard computer and in command unit on basis of computational algorithms introduced in their storage and data received from sensors with dangerous and limiting magnitudes; in case these magnitudes are beyond limiting magnitudes, limiting and dangerous commands are formed and are transmitted to onboard computer and to emergency information system of aircraft for recording and warning the crew. Magnitudes of actual operating hours and remaining service life of aircraft engine are determined in onboard computer and are transmitted to onboard information system for recording and indication.

EFFECT: enhanced efficiency of monitoring of aircraft engine working at augmented power rating and increased thrust.

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