ONBOARD MONITORING SYSTEM OF AIRCRAFT ENGINE AT LIMITED TEMPERATURE, PRESSURE AND THRUST

FIELD: aircraft instrumentation engineering; monitoring of gas-turbine engines. ^ SUBSTANCE: proposed monitoring system makes it possible to check 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 and transmitted to inputs of multiplexing unit and from output of this unit to onboard computer. Information received from sensors indicating very important parameters of aircraft engine is fed directly to command unit input on basis of computational algorithms and information received from sensors pertaining to very important parameters of aircraft engine, viz.: turbine exhaust gas temperature, pressure of gas after fan doors and thrust; these magnitudes are compared with limiting and dangerous magnitudes in onboard computer and in command unit; in case these magnitudes are beyond limiting and dangerous magnitudes, limiting and dangerous command 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 onboard monitoring of aircraft engine working at augmented power rating and increased thrust. ^ 2 dwg