FIELD: engines and pumps.
SUBSTANCE: gas turbine diffuser comprises two circular baffles extending inside each other and connected by, in fact, radial vanes. Lower peripheral edge of one of said baffles comprises cutouts regularly distributed along diffuser lengthwise axis. Invention covers also gas turbine engine, in particularly, aircraft turbojet or turbo-prop, comprising aforesaid diffuser and annular combustion chamber arranged downstream of diffuser and inside engine outer housing. Fuel is forced into combustion chamber by injectors arranged between diffuser and combustion chamber to extend, in fact, radially inside inner space from outer housing. Cutouts of downstream peripheral edge of said or every diffuser baffle are leveled axially with injectors to allow upstream shift of every injector in said cutout for removal of said injector.
EFFECT: decreased axial size of turbine and its weight.
14 cl, 7 dwg
