FIELD: motors and pumps.
SUBSTANCE: invention relates to the aviation and ground application gas turbine engines multistage turbines rotors. Multi-stage turbine rotor includes first, middle and last discs, which are through the spherical washer and elastic element tightened with the shaft by the central clamping bolt. By the radial annular flange the last disk is installed on the shaft, and the first disk is made with the radial flange. With the outer surface the elastic element is installed in the first disc Z-shaped front flange and contacts with it by the end face, with the inner surface its is mounted on the clamping bolt. Elastic element is fixed relative to the first stage disc front flange in the circumferential direction by the axial pins and is made with L-shaped annular flange with the clamping bolt retainer in the circumferential direction installation thereon. Closest to the first disk hub elastic element surface is made flat.
EFFECT: invention allows to increase the gas turbine engine multi-stage turbine rotor reliability by the elastic element contact with the disk blade or hub elimination during the gas power turbine rotor operation.
1 cl, 2 dwg
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