GAS TURBINE STATOR Russian patent published in 2014 - IPC F01D25/24 

FIELD: machine building.

SUBSTANCE: gas turbine stator comprises an outer case with nozzle blade units set as per the gas flow with the split ring segments being placed between the latter. The nozzle blade units in axial direction are fixed by an L-shaped locking ring by radial ribs, and in the circumferential direction - by axial protrusions of the outer case located between the radial ribs of the nozzle blade units. The split ring segments are mounted by front tails in the radial direction between the axial protrusions of the L-shaped locking ring and axial protrusions of the nozzle blade units. In the circumferential direction the split ring segments are installed so that to form grooves between the radial ribs of the nozzle blade units and are fixed by means of the axial protrusions. The split ring segment protrusions are placed on the side of the wheel space and are directed towards the axial protrusions of the outer case. The front tail of each split ring segment is located so that the ratio of the distance between the tail of the split ring segment and the groove bottom to the transition radius from the groove bottom to the side wall of the radial rib of the nozzle blade unit amounts to 1.1-3.

EFFECT: higher reliability of a gas turbine stator.

2 cl, 3 dwg