Experimental study on blade dynamic stress of high loading ten-stage axial compressor was conducted. The results show that dynamic static pressure at exit of rotor blade increases quickly when surge happens, followed by dynamic strain to its summit in 0.1 second. Second order of blade dynamic stress exceeds the limitation of fatigue and may produce fatigue damage. Exit dynamic static pressure has relationship both with second order of blade frequency and blade passing frequency in the form of the fraction of forward and backward waves. And the waves are not the fixed nodal. Numerical analysis of flutter shows accumulated work is less than zero and logarithmic damping is more than zero from the first to the third order of blade frequency. Blade thickness is increased, and then blade frequency is added in order to improve anti-vibration ability of blade. The relative maximum thickness (maximum thickness divided by chord) at the root of blade increased from 0.076 to 0.089. The resonance speed of the first order of blade (bending vibration) increases 15.2 percent. The test shows the relative dynamic strain decreases 18 percent at the corrected speed of 75 percent when it surges. The method of improving blade frequency has solved the issue of blade dynamic stress burst increasing when the compressor surges.