The vibration localization is caused by mistuned of blade, then it will develop high cycle fatigue in local blade of the aero-engine bladed disk system. The method of increasing friction existing in blade root is used, which decrease the amplitude and vibration localization degree of bladed disk system. Based on a microslip friction model, the constitutive relation of damper friction force is formulated. The hysteresis loop expressing force and displacement relation of damper is instead by a equivalent oval. And the equivalent damp and stiffness are calculated, they can be acted on lumped mess model of bladed disk system. Dynamics equation is established in single sector with 3-DOF. The harmonic balance method is applied to analysis vibration characteristics, and the effect of dry friction on vibration properties of mistuned bladed disk system is discussed. The results show that resonance peak value can be decreased remarkably by the friction existing the blade roots. Meanwhile, comparing the position of resonance peak between the system with friction and without, it is found that the first one is hysteretic. The degree of vibration localization can be decreased effectively by increasing blade root friction.