The invention relates to the field of main combustion chamber design of an aero-engine, in particular to a standing vortex cavity rotational flow atomization device for a head of a flame tube. The standing vortex cavity rotational flow atomization device comprises an outer swirler, a nozzle shell body, a supporting rod, a standing vortex cavity, an inner swirler, a main oil pipe, an auxiliary oilpipe and a fuel pipe, wherein the nozzle shell body comprises an outer cylinder, a middle cylinder body and an inner cylinder, a main nozzle is formed in the wall surface of the outer cylinder, a cooling through hole is formed in the wall surface of the standing vortex cavity, a middle air flow channel is formed between the outer cylinder and the outer swirler, a main oil cavity is formed betweenthe outer cylinder and the middle cylinder body, an auxiliary oil cavity is formed between the middle cylinder body and the inner cylinder, and an air inlet channel is formed between the inner cylinder and the standing vortex cavity. The device has the advantages that the structure is simple, staged combustion of an main combustion chamber of the aero-engine, and the defects in the prior art are solved.