| 摘要 |
FIELD: motors and pumps.SUBSTANCE: turbojet turbine comprises stator, high and low pressure rotors with placed between them inter-shaft sealing containing the flange installed on the shaft of the high pressure rotor, and its companion labyrinth on the low pressure rotor shaft. The flange is designed as S-shaped in the cross-section and is located from inside the rotor labyrinth mounted on the liner of the high-pressure rotor shaft and fixing in the axial direction by means of thread liner an internal ring of the roller bearing of the high-pressure rotor. The flange is fixed in radial direction by the cylindrical internal surface of the rotor labyrinth, and in axial direction - by face surface of the liner of the shaft of the high-pressure rotor, from the one side, and located on the rotor labyrinth by lock expander ring, from the other side. Front and back with reference to the gas flow liners of the flange by means of slits are connected respectively with the shaft of the high-pressure rotor and rotor labyrinth. Companion with the flange the labyrinth on the shaft of the low pressure rotor is designed with a cylindrical axial ring-type rib plastically deformed and installed with the thrust against the chamfers of the shaft of low pressure rotor.EFFECT: invention allows to improve reliability and maintainability of the turbojet engine turbine.3 dwg |
