GAS-TURBINE ENGINE COMBUSTION CHAMBER Russian patent published in 2004 - IPC

FIELD: annular combustion chambers for gas-turbine engines. SUBSTANCE: proposed combustion chamber has housing with combustion liner inside it; combustion liner consists of two circular envelopes connected together by means of pre-chamber including fuel injectors. Each fuel injector is made in form of body-strut oriented in plane running through longitudinal axis of combustion liner or near this axis; it is provided with two burner modules provided with radial air swirler each. Burner modules form two concentric rows in cross section of combustion liner. Burner modules are located in different rows in each injector on different sides from plane passing through body-strut of fuel injector. Distance between center of each burner module of inner row and centers of two nearest burner modules of inner and outer rows is identical. Distance between c enter of each burner module of outer row and centers of two nearest burner modules of inner row is equal to distance between centers of burner modules of inner row. EFFECT: enhanced economical efficiency; increased service life of gas turbine. 2 cl, 3 dwg