Gas turbine combustion chamber axial two-stage swirl nozzle

A gas turbine combustion chamber axial two-stage swirl nozzle is technically characterized in that a two-stage axial swirl device is arranged in the axial direction in a peripheral axial annular air channel. A first-stage swirl device is fixed on a center cone body, and a gap is reserved between the top of the first-stage swirl device and the outer wall face of the nozzle. A second-stage swirl device is arranged on the downstream of the first-stage axial swirl device and fixed on the outer wall face of the annular air channel, and a gap is reserved between the bottom and the center cone body. Two stages of swirl vanes are arranged in a staggering mode. The swirl angle of the second-stage swirl device is larger than that of the first-stage swirl device. The nozzle can ensure the swirl strength on the peripheral side of the inside and the outside of the air channel, the swirl on the inner peripheral side of the air channel is weak in strength, and the axial speed of the air flow can be increased. The swirl on the outer peripheral side of the air channel is high in strength, the combustion area can be controlled reasonably by matching the nozzle outlet speed distribution and the fuel air blending effect, the inner flowing field structure of the combustion chamber is maintained, and combustion stability and good outlet temperature distribution can be ensured.