GAS TURBINE COMBUSTOR Russian patent published in 2018 - IPC F23R3/48 

FIELD: turbines or turbomachines.

SUBSTANCE: combustion chamber of a gas turbine with a structure including a plurality of combustion chambers of a gas turbine, the flame-transfer nozzle connects adjacent combustion chambers to each other. Combustion chambers include combustion chamber sections having combustion air channels on their outer circumferential surfaces. Flame transfer nozzle has a double nozzle design including an internal nozzle that connects the combustion chamber sections of the adjacent combustion chambers to each other, and an external branch pipe that spans the inner branch pipe and connects the air channels for combustion of adjacent combustion chambers among themselves. In addition, the flame transfer nozzle has windows located between the inner tube and the outer nozzle on the outer circumferential partition walls of the combustion air ducts communicating with the outer branch pipe of the flame tube, around the inner pipe. Windows allow the combustion air to pass through the inner pipe portions on the upstream side and downstream side with respect to the combustion air flow passing through the air ducts. Flame transfer nozzle further includes guide plates mounted on the upstream portion of the inner tube. These guide plates provide the direction of the combustion air through the window into the space inside the outer sleeve.

EFFECT: invention is directed to cooling the flame tube during ignition in the combustion chamber of a gas turbine and to reduce emissions of nitrogen oxides and unburned hydrocarbons, such as carbon monoxide, from a gas turbine.

9 cl, 6 dwg