MULTISTAGE TURBINE ROTOR

FIELD: power and transport engineering. SUBSTANCE: invention can be used in turbines of aircraft engines and gas-turbine plants of ground application. Proposed rotor of multistage turbine is provided with disks arranged in cantilever manner relative to supports and braced together with shaft by central bolt. Disks are furnished with flanges extended in axial direction. Flanges of neighbor disks being in contact over end face surfaces are aligned and fixed by precision pins. Shaft is provided with radial-conical envelope with attachment flange, -shaped in section. Narrowing of conical section of envelope is pointed to connecting flange which is attached to flange of nearest disk. Flexible member in form of plate spring is placed between bracing bolt and plane of disk of first stage. Disks can be aligned by center by means of intermediate part, for instance, diaphragm. EFFECT: increase reliability and rigidity of structure owing to prevention of loosening of rotor pack and unbalancing at cyclic loads and approach of rotor front support to its gravity center. 2 cl, 2 dwg