Structure of centrifugal compressor impeller of aviation turbojet engine

The invention relates to the field of compressor impeller design, in particular to an aviation turbojet engine centrifugal compressor impeller structure which comprises an impeller base body, a hole is formed in the center of the impeller base body, a shaft sleeve is arranged in the center of the impeller base body, the inner wall of the shaft sleeve is of a polygonal structure, and blades are evenly distributed on the impeller base body and comprise large blades and small blades. The large blades and the small blades are distributed alternately; the air compressor has the advantages that the impeller of the air compressor is designed to be of a large and small blade structure, the optimal large and small blade size is provided, airflow separation can be effectively restrained or even eliminated, airflow blocking is avoided, airflow can pass through the air compressor more smoothly, high pneumatic stability can be kept through the large and small blade technology, and the service life of the air compressor is