FIELD: engines and pumps.
SUBSTANCE: invention relates to aircraft engine production and can be used in gas turbine engine electronic mechanical ACS. In compliance with this invention, to identify compressor surge state, engine fan rpm is additionally analysed, as well as engine inlet temperature and pressure. In case simultaneous increase in fan rpm and engine inlet pressure and temperature and pressure drop at engine inlet and increase in air temperature at engine inlet are observed with gradient exceeding 2 to 3 times preset tolerances specified in aircraft operating performances, signal "Surge" will be generated.
EFFECT: higher engine reliability and aircraft safety.
1 dwg
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