ROTOR OF MULTISTAGE COMPRESSOR Russian patent published in 2003 - IPC

FIELD: mechanical engineering. SUBSTANCE: invention relates to rotors of multistage compressors of small-size gas-turbine engines. Rotor of multistage compressor contains rigidly interconnected disks 1 with fitted-on blades 2 coupled with drive shaft 3 by means of conical diaphragm 4 located at compressor outlet. Blades 2 of last stage are installed on upper part of diaphragm 4. Bulge 5 is made in middle part of diaphragm 4 at side pointed to disks, said bulge being engaged with additional radially arranged disk 6. Ring longitudinal projections 7 with lips of gas labyrinth seal are made, one over the other, on outer side of diaphragm 4. EFFECT: reduced weight and overall dimensions of rotor. 2 cl, 1 dwg