FIELD: engines and pumps.
SUBSTANCE: invention relates to aircraft engine production and can be used in gas turbine engine automatic control systems (ACS) built around electronic and hydro mechanical components. The invention consists in that the stand-by hydro mechanical controller generates a preset engine rotor rpm value, invariable for the given engine, the said rotor actual rpm is measured to be compared to the aforesaid preset one, the obtained difference allowing varying the turbine blades position till the preset rpm becomes equal to the actual rpm.
EFFECT: gas turbine engine higher reliability and aircraft safety.
1 dwg
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