The invention belongs to the technical field of turbine engines for small missile/unmanned aerial vehicles, and specifically relates to a double-oil-channel centrifugal nozzle structure adopting an integrated design of a main oil channel and an auxiliary oil channel. The double-oil-channel centrifugal nozzle structure comprises a main oil tube, an auxiliary oil tube, a nozzle rod, a locking sheet, a fixing nut, an auxiliary oil channel hydrocyclone, a main oil channel nozzle and an auxiliary oil channel nozzle. The double-oil-channel centrifugal nozzle structure disclosed by the invention and adopting the abovementioned technical scheme is simple and reliable; and test results indicate that the arrangement of an opening point of the main oil channel is reasonable, the double-oil-channel nozzles can meet the requirement of a high-flow adjustment ratio, the spray cone angles of the main oil channel and the auxiliary oil channel are reasonable, and fuel oil atomization of the main oil channel and the auxiliary oil channel in the whole working whole course of an engine meets a use need.