Abstract: Based on the theory of aerodynamic damping,the appropriate damping model was established;with the help of moving meshes technology and in combination with the equation of equivalent mode aerodynamic damping ratio,the weakly coupled method was applied.In the researches of Rotor 37 transonic blade with excitation of the 1st bend mode,the 1st torsion mode and the 1st bend-torsion mode,the aerodynamic damping was gained.The pressure and the blade amplitude were considered.The results demonstrate that when the pressure ratio of input pressure and output pressure has been fixed,aerodynamic damping has a linear relation with the pressure;with a small blade deformation,the blade deformation has little influences on aerodynamic damping.