FIELD: engines and pumps.
SUBSTANCE: invention can be used in electronic hydro mechanical automatic control systems (ACS) intended for gas turbine engines (GTE). At inlet guide vane (IGV) blade position sensor failure actual air compression ratio in compressor is defined by measured air pressure at engine input and behind engine compressor, specified compression ratio value is formed by measured frequency of engine rotor rotation and air temperature at engine input, value of discrepancy between specified and measured compression ratio values helps forming control action at IGV blade drive and change IGV position till actual compression ratio is equal to specified.
EFFECT: increase of electronic hydro mechanical systems efficiency, improvement of gas-turbine engine security and aircraft safety.
1 dwg
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