Axial force balancing structure for aero-engine compressor test

The invention belongs to the technical field of aero-engine compressor test axial force balance design, and particularly relates to an aero-engine compressor test axial force balance structure which is used for balancing the forward axial force of a compressor, airflow generating pressure difference comes from the compressor, the magnitude of the generated pressure difference can change along with the flow of the compressor, and the axial force of the compressor is balanced. By designing the sizes of the front balance disc, the rear balance disc, the air entraining hole and the air exhaust hole, the generated backward thrust can be matched with the forward axial force of the air compressor in various working states, is prevented from being too large or too small, and has higher self-adaptive capacity, so that the air compressor test can be effectively ensured to be smoothly completed. 本申请属于航空发动机压气机试验轴向力平衡设计技术领域，具体涉及一种航空发动机压气机试验轴向力平衡结构，以其对压气机前向轴向力进行平衡，产生压差的气流来自于压气机，其产生压差的大小能够随压气机流量发生变化，可通过对前部平衡盘、后部平衡盘以及引气、排气相关