GAS-TURBINE ENGINE CONTROL AND PARAMETER MONITORING SYSTEM Russian patent published in 2007 - IPC F02C9/00 

FIELD: aircraft industry.

SUBSTANCE: invention relates to automatic control systems of aircraft gas-turbine engines. According to invention, system contains signaling unit, readjustment level unit, failure signal forming unit, unit of "n" AND input gates, unit of communication with actuators, setting former unit, monitoring unit, first unit and AND gates, OR gate, counter AND gate, NOT gate, program unit, first switch, analogue-to-digital converter, pickup check unit, speed failure unit, second AND gate unit, speed metering unit, check frequency setter, starting unit, enable signal unit. System includes additionally second switch, digital-to-analogue converter unit and computer unit. Introduction of additional devices into system provides uninterrupted calculation of speed (tendency) of change of parameters, relationship of parameters depending on engine operation mode, for instance, relationship between air pressure after high-pressure turbine and air pressure in space after labyrinth of high-pressure turbine depending on engine speed and putting out signals to actuators if relationship of pressure values gets out of limit range.

EFFECT: enlarged functional capabilities and provision of reliable information as to parameters of gas-turbine engine and transmission of results of calculation to emergency recording system.

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