FLAME TUBE FOR RING COMBUSTION CHAMBER OF GAS-TURBINE ENGINE HAVING CENTRIFUGAL COMPRESSOR Russian patent published in 1995 - IPC

FIELD: aircraft engineering. SUBSTANCE: flame tube has a front unit constructed as a radial blade swirler having the centrifugal nozzle positioned at the center. The nozzle is interposed between the outer and internal ring shells. Each shell has at least two rows of openings arranged over the length. The openings are used for supplying secondary air. Axes of the openings of the internal shell are positioned in the radial planes passing through longitudinal axis of the nozzle. Axes of the openings of the outer shell are arranged in the radial planes inclined to the radial planes passing through longitudinal axes of the nozzle at 9-15° angle. EFFECT: improved design. 2 dwg