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

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

SUBSTANCE: proposed system employs information received from aircraft parameter sensors and transmitted to multiplexing unit inputs and from output of this unit to on-board computer. Information received from sensors of very important parameters of engine is transmitted directly to command unit input. Measured present magnitudes are compared with specified limiting and dangerous magnitudes in on-board computer and in command unit on basis of algorithms introduced in their storage and information pertaining to dangerous parameters of aircraft engine: rotational speed of high-pressure compressor rotor, turbine outlet temperature, pressure of gas after fan doors 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 recording and warning the crew. Actual operating time and residual service life with commands thus obtained taken into account are determined in on-board computer and are transmitted to on-board information system for indication and recording.

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

2 dwg