Non-adjustable stator blade assembly structure of gas compressor in aero-engine

The invention belongs to the technical field of design of non-adjustable stator blades of gas compressors in aero-engines, and particularly relates to a non-adjustable stator blade assembly structure of a gas compressor in an aero-engine, which is characterized in that sealing vibration reduction pieces are arranged in lower margin plate mounting grooves on the outer sides of arc-shaped sections of a stator inner ring; according to the sealing vibration reduction device, the sealing vibration reduction pieces are arranged on the fan-shaped sections and the arc-shaped sections of the non-adjustable stator blades, so that gaps between the fan-shaped sections and the arc-shaped sections of the non-adjustable stator blades are blocked, and therefore inward leakage of airflow can be reduced, and pneumatic losses are reduced; the edges of the two sides are attached to the inner side of the lower edge plate of the fan-shaped section of the non-adjustable stator blade and the outer side of the arc-shaped section in a