GAS TURBINE COMBUSTION CHAMBER Russian patent published in 2003 - IPC

FIELD: gas turbines. SUBSTANCE: proposed combustion chamber of gas chamber includes burner liners connected with circular gas receiver which is fastened with outer and inner casings. Each burner liner has front wall at outlet in direction lateral relative to flow; this wall is secured to wall of burner liner and is connected with gas receiver. Located above front wall in way of flow are branch pipes and prechamber with blades swirlers. Wall of burner liner is provided with several slots which are inclined to longitudinal axis of prechamber; lower edges of these slots are located between branch pipes in one meridian plane in way of flow. Upper edges of said slots are located above branch pipes in way of flow in other meridian plane. Angle of inclination of projection of longitudinal surfaces of inclined slots to longitudinal axis of prechamber ranges from 30 to 75 deg. Longitudinal surfaces of inclined slots are located across angles of swirler blades relative to longitudinal axis of prechamber and/or across direction of flow of combustion products twisted by bladed swirlers. EFFECT: reduction of toxicity of turbine exhaust gases. 2 cl, 3 dwg