| 摘要 |
FIELD: aircraft instrumentation engineering; onboard 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 parameters and transmitted to inputs of multiplexing unit and from output of this unit to onboard computer. Information received from sensors pertaining to very important parameters of aircraft engine is fed directly to command unit input. Information received from sensors of very important parameters of aircraft engine, viz.: rotational speed of high-pressure compressor rotor, turbine exhaust gas temperature and thrust are compared in onboard computer and in command unit on basis of computational algorithms introduced in their storage and received from sensors with limiting and dangerous magnitudes; 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 for warning the crew. Magnitudes of actual operating hours of aircraft engine and remaining service life are determined in onboard computer with the received commands taken into account and are transmitted to onboard information system for indication and recording. ^ EFFECT: enhanced efficiency of onboard monitoring of aircraft engine working at augmented power rating and increased thrust. ^ 2 dwg |
