FIELD: aircraft engine building.
SUBSTANCE: invention relates to aircraft engine building, in particular to control devices in control systems for radial clearances of gas turbine engines. The electric damper contains a housing with a damper made rotary driven by an electromechanism and a stop for fixing the position of the rotary damper in the closed position, a return mechanism, an electromechanism with an electric motor, a planetary gear, a control and monitoring unit. The electric motor of the electromechanism is made with a rotor with incorporated permanent magnets and is made of a two-phase magnetic material, moreover, non-magnetic zones are distributed along the circumference of the rotor in the area between the incorporated permanent magnets and pole pieces, and at least two damper position sensors are installed in the electromechanism.
EFFECT: reducing the weight, improving the manufacturability of the device, reliability and material utilization, as well as improving the positioning accuracy of the damper.
1 cl, 2 dwg
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Authors
Dates
2023-03-02—Published
2022-07-25—Filed