LOCATION OF COMBUSTION CHAMBER BURNERS Russian patent published in 2018 - IPC F23D11/12 F23R3/04 F23R3/14 

FIELD: power industry.

SUBSTANCE: burner (30) for a gas turbine combustion chamber (16) comprises a body (53) having a surface (64) and a burner axis (50), a fuel pipe (56), an igniter (58) and a passage (62) or passages (62) for the primary airflow. The passage (62) or passages (62) for the primary airflow are inclined relative to the burner axis (50) and create a primary vortex around the burner axis (50) in the first rotation direction. The primary vortex moves in the direction along the burner axis (50) and from the surface (64). The igniter (58) is located downstream after the fuel pipe (56) relative to the first rotation direction of the primary vortex so that part of the primary airflow (34A) passes above the fuel pipe (56) and then above the igniter (58). The fuel pipe (56) comprises a fuel pipe axis, a tip for liquid fuel having an outlet for fuel, and a lattice of auxiliary air passages having outlets arranged around the fuel outlet. The auxiliary air passages are inclined relative to the fuel pipe axis to create a vortex of auxiliary air around the fuel pipe axis in the same rotation direction relative to the first rotation direction. The auxiliary air passages are radially inclined at an angle relative to the axis of the fuel pipe.

EFFECT: invention allows to prevent formation of deposits on the burner parts, improve the reliability of fuel ignition in the combustion chamber and the quality of liquid fuel atomization.

15 cl, 10 dwg