MULTISTAGE GAS TURBINE Russian patent published in 2005 - IPC

FIELD: multistage gas turbine of aircraft and ground application.

SUBSTANCE: according to invention, in multistage gas turbine with higher pressure relief chamber at outlet limited over periphery by labyrinth seal, said seal is made multistage, air space between first and second side from relief chamber stages of labyrinth seal is connected with gas chamber before last disk of turbine by channels made under feed of locks of working blades of last stage and slot spaces between ring flange on rim of disk of last stage and rim of disk from side of inlet in direction of gas flow at F₁/F₂=3...10 where F₁ is passage area of first stage of labyrinth seal, and F₂ is area of slot spaces.

EFFECT: improved reliability of multistage gas turbine owing to provision of effective cooling of last stage disk rim and disk-to-working blade lock joint.

2 dwg