The invention provides an aviation engine blade forging method and a die. The aviation engine blade forging method comprises the following steps that firstly, a blank is discharged; secondly, a glasslubricant is sprayed to the surface of the blank; thirdly, the blank is heated to the recrystallization temperature or above, and the temperature is kept; fourthly, the blank is put into a preheated extrusion cavity of the die, rod extruding is carried out, and an extrusion rod piece is obtained; fifthly, after rod extruding is completed, the extrusion rod piece is put into a heading cavity of thedie within 4 s-6 s, heading is carried out, and a heading piece is obtained; sixthly, after heading is completed, the heading piece is put into a finish forging cavity of the die within 4 s-6 s, final forging is carried out, and a blade is obtained. Due to the fact that the extrusion cavity, the heading cavity and the finish forging cavity are formed in the same die, the time interval between rodextruding and heading and the time interval between the heading and the finish forging are extremely short, the temperature of the extrusion rod piece and the temperature of the heading piece are reduced limitedly, and in the whole forging process, only one time of heating is needed for the blank.