Aiming at the problems that the resonance characteristics of aero?engine turbine blades may lead to fatigue fracture and vibration failure of the blades, this paper takes a certain type of aero?engine turbine blade as the research object to carry out resonance margin analysis research. Firstly, the vibration characteristics of the blade are analyzed simultaneously based on the test self?hammering method and the finite element physical simulation calculation method, and the correctness and practicability of the model are verified by extracting the modal analysis results of the first six orders of the blade under the two working states. Secondly, on the basis of the existing model, by drawing the Campbell resonance curves at different working speeds and combining with the actual working parameters of this type of engine, the check and analysis of the speed resonance margin is carried out. The rotational speeds at which resonance may occur on the blades are analyzed and the optimization and improvement plan is proposed. This method mainly provides sufficient scientific basis and methods for the preliminary design and manufacture of the blade and the resonance safety inspection.