FIELD: engines and pumps.
SUBSTANCE: combustion chamber of the gas turbine engine comprises a housing, a flame tube, a burner plate and nozzles, a fuel manifold ring and at least one means for activating air by laser radiation. The fuel manifold ring is installed in the front cavity on the burner plate and a fuel line is connected to it. Each means of air activation is installed outside the housing, the air outlet pipe is connected to it from the last stage by the compressor. An air manifold ring is installed in front of the fuel manifold ring and an activated air supply line is connected to it, the input of which is connected to the outlet of the air activation means. The activation means is made in the form of a housing with a system of mirrors installed inside it and a laser unit mounted on the housing.
EFFECT: increased reliability of the means of air activation and ensured maintainability.
13 cl, 13 dwg
