GAS TURBINE COMBUSTION CHAMBER Russian patent published in 1999 - IPC

FIELD: mechanical engineering. SUBSTANCE: gas turbine combustion chamber passes compressed air swirled relative to axis and flowing from compressor part to turbine part. Ring channel is provided at combustion chamber inlet with intake part to separate partial flow from main flow. Intake part has means to eliminate swirling of partial flow and it is placed in communication with cooling channels for cooling combustion chamber and with pilot burners for stabilizing burning process in combustion chamber. EFFECT: reduced thermodynamic losses, possibility of using separated partial flow, both for cooling and for stabilization. 8 cl, 1 dwg