ONBOARD MONITORING SYSTEM FOR ENGINE AT LIMITED TEMPERATURE, FUEL PARAMETERS AND PRESSURE Russian patent published in 2005 - IPC

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

SUBSTANCE: proposed system operates on basis of information received from sensors of aircraft engine parameters and transmitted to inputs of multiplexing unit and from outputs of this unit to onboard computer. Information received from sensors of very important parameters of aircraft engine is transmitted directly to command unit input. Measured present magnitudes of sensor signals are compared with limiting and dangerous magnitudes in onboard computer and in command unit on basis of computational algorithms introduced in their memory and information received from sensors: turbine exhaust gas temperature, consumption and pressure of fuel, pressure of gas after fan doors. In case these magnitudes are beyond limiting and dangerous magnitudes, limiting and dangerous commands are formed and are transmitted to onboard computer and to aircraft emergency information system for recording and warning the personnel. Actual operating hours and residual operating hours of engine are determined in onboard computer with received commands taken into account and are transmitted to onboard information system for indication and recording.

EFFECT: enhanced efficiency of monitoring aircraft engine in standard, off-standard and augmented power rating modes.

2 dwg