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

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

SUBSTANCE: proposed monitoring system makes it possible to check technical state of aircraft engine 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 is transmitted directly to command unit input. Measured present magnitudes are compared with limiting and dangerous magnitudes in onboard computer and in command unit on basis of computational algorithms introduced in their storage and received from sensors of very important parameters, viz.: rotational speed of high-pressure compressor, pressure of gas after fan doors and thrust. In case these magnitudes are beyond limiting and dangerous 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 with the received commands taken into account 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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