ON-BOARD AIRCRAFT ENGINE MONITORING SYSTEM AT LIMITATION OF ROTATIONAL SPEED, TEMPERATURE, PRESSURE AND THRUST Russian patent published in 2005 - IPC

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

SUBSTANCE: proposed system employs information transmitted from sensors of aircraft engine parameters to inputs of multiplexing unit and from output of this unit to on-board computer. Information received from sensors of very important parameters of aircraft engine is transmitted directly to command unit input. Present measured magnitudes are compared with limiting and dangerous magnitudes in on-board computer and in command unit on basis of algorithms introduced in their storage and information received from sensors pertaining to dangerous magnitudes of aircraft parameters: rotational speed of high-pressure compressor, turbine outlet temperature, consumption and pressure of fuel and thrust. In case of deviation of these magnitudes from specified limits, limiting and dangerous commands are formed and are transmitted to on-board computer and to emergency information system for warning the crew. Actual operating time and residual service life of aircraft engine are determined in on-board computer with commands thus obtained taken into account and are transmitted to on-board information system for indication and recording.

EFFECT: possibility of monitoring the aircraft engine in standard, off-standard and augmented power rating conditions.

2 dwg