Cavity pressure test structure for air system of aero-engine

The invention belongs to the technical field of aero-engine air system cavity pressure test design, and particularly relates to an aero-engine air system cavity pressure test structure comprising an air system side wall provided with a cavity pressure measuring hole; the air inlet end of the air pipe is located on the inner side of the side wall of the air system and attached to the inner side of the side wall of the air system, the air pipe is partially semicircular and bent, and the end is tilted. The air outlet end of the air pipe extends out of the cavity pressure measuring hole; the pressing pieces are arranged on the inner side of the side wall of the air system in a spot welding mode, the air inlet end of the air pipe is tightly pressed on the inner side of the side wall of the air system, and one pressing piece is pressed on the top of the semicircular bent portion of the air inlet end of the air pipe. 本申请属于航空发动机空气系统腔压测试设计技术领域，具体涉及一种航空发动机空气系统腔压测试结构，包括：空气系统侧壁，其上具有腔压测量孔；空气管，其进气端位于空气系统侧壁内侧，贴靠在空气系统侧壁内侧，局部