Intermediate blade of air compressor used for high power gas turbine

The utility model discloses an intermediate blade of an air compressor used for a high power gas turbine, and relates to a blade of an air compressor used for a high power gas turbine, aiming at solving the problems that the intermediate blade of the air compressor used for the high power gas turbine is low in efficiency and short in service life, and affects the safe operation of the air compressor. The geometry data of the sections from the root to top of the working part of the blade is as follows: the height H between a section A-A to a section F-F is 0-170.688mm, the axial width B is 57.736-41.885mm, the bending angle is 43.169 degrees to 57.963 degrees, the maximum thickness Dmax of molded lines is 10.509-5.481, and the thickness DE of a venting edge with a distance of h from venting edge is 1.078-0.628mm, wherein h is equal to 0.7mm, the total height L of the working part of the blade is 158.67mm, the chord length b at the section A-A is 77.723mm, the chord length b at the section A-A is 77.723mm, the chord length b at the section B-B is 77.725mm, the chord length b at the section C-C is 77.724mm, the chord length b at the section D-D is 77.740mm, the chord length b at the section E-E is 77.724mm, and the chord length b at the section F-F is 77.724mm. The intermediate blade is used on the air compressor used for the high power gas turbine.