GAS TURBINE WITH NOZZLE CASE TIGHTLY JOINTED TO COMBUSTION CHAMBER END FACE Russian patent published in 2009 - IPC F01D9/02 F23R3/60 

FIELD: engines and pumps.

SUBSTANCE: gas turbine comprises annular combustion chamber with inner and outer walls, high-pressure turbine nozzle case and fasteners to attach the latter to combustion chamber inner and outer wall end faces. High-pressure turbine nozzle case comprises fixed vanes distributed around combustion chamber axis. Each vane has airfoil section rigidly fixed with inner and outer flanges that represent circular sectors butt-jointed together to constrict gas flow section inside nozzle case. Rear end parts of inner and outer walls of combustion chamber are pressed against inner and outer flanges of turbine nozzle case, right up to the flange read edge. Aforesaid fasteners are formed by screws arranged radially to enter nozzle case airfoil sections through holes in the combustion chamber inner and outer wall rear end parts.

EFFECT: higher tightness of gas flow channel.

10 cl, 5 dwg