FIELD: engines and pumps.
SUBSTANCE: invention relates to aircraft engine production and can be used in gas turbine engine (GTE) automatic control systems (ACS). Essence of invention consists in the fact that, in addition, the computing device is made in the form of space cam the first inlet of which is connected to air pressure gauge at compressor inlet, and the other one - to hydraulic cylinder of drive of inlet guide vane (IGV) blades, and outlet - to comparison device the second inlet of which is connected to outlet of air pressure gauge after compressor.
EFFECT: improving operating quality of control device, improving GTE operating reliability and aircraft safety.
1 dwg
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