GAS TURBINE SYSTEM, WHICH REDUCES STRESS Russian patent published in 2017 - IPC F01D5/08 F01D5/30 

FIELD: machine engineering.

SUBSTANCE: turbine system includes a rotor blade with a shank and a turbine disc comprising a slot, in which a shaft of the rotor blade is fixed. Slit of the turbine disk comprises a plurality of opposed pairs of slits of the projections, a plurality of opposite pairs of recesses and the bottom of the slot gap. The bottom of the slot comprises a first portion of a convex surface. The shank of the rotor blade comprises a bottom shank having a first portion of the concave surface corresponding to the first portion of the convex surface of the bottom slit. The first part of the convex surface is permeated by an outlet of cooling channel, which is passing through the turbine disk. Another invention of the group relates to a gas turbine comprising the above turbine system.

EFFECT: reduction of stress concentration at the bottom of the disk slot having a cooling passage.

9 cl, 5 dwg