The invention provides an anti-backfire nozzle for a rocket engine. The anti-backfire nozzle comprises a rotary core body (1), an anti-backfire ring (2) and a shell (3); the anti-backfire ring (2) is arranged between the rotary core body (1) and the shell (3); the inner wall face and the outer wall face of the anti-backfire ring (2) cling to the outer wall face of the rotary core body (1) and the inner wall face of the shell (3) respectively; a liquid propellant storing and distributing cavity (11), a tangential hole (12) and a swirl chamber (13) are formed in the rotary core body (1); the shell (3) is provided with a nozzle exit (31) and a thermal insulation material (32); and a propellant flows along a flowing passage defined by the anti-backfire ring (2), the liquid propellant storing and distributing cavity (11), the tangential hole (12), the swirl chamber (13) and the nozzle exit (31), is uniformly distributed and shunted by the liquid propellant storing and distributing cavity (11), forms uniform conical mist spray at the outlet of the nozzle exit and is atomized. The anti-backfire nozzle has the advantages of simple structure, mature process and the like, has both the functions of backfire resistance and efficient combustion and is suitable for other engines and combustion devices with high requirements on performance and easiness in generating backfire.