An air swirling device arranged in the nozzle of a gas turbine combustor
A swirl device, gas turbine technology, applied in the direction of combustion chamber, continuous combustion chamber, combustion method, etc., can solve the problems of small air deflection angle, weak swirl strength, poor mixing effect of fuel and air, etc., and achieve wide design space, improved combustion reliability, and improved velocity distribution
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[0018] The principle, structure and specific implementation of the present invention will be further described below in conjunction with the accompanying drawings.
[0019] figure 1 , figure 2 and image 3 It is a schematic diagram of the structural principle of a gas turbine combustor nozzle equipped with an air swirl device. The air swirl device is arranged upstream of the central cone 3 in the peripheral annular air channel 2. The air swirl device 4 adopts an axial vane structure. It is best to adopt a hollow axial vane structure, which is evenly arranged along the peripheral annular air passage 2, and communicates with the central fuel passage 1 through the fuel injection hole 6, and the number of vanes is generally between 6 and 12.
[0020] The blade of the air swirl device 4 is provided with a notch 5, and the starting position is located at the bending angle change point 7 on the suction side of the blade. The intersection 8 of the cutting surface 13 of the notch 5 ...
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