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There are three stages of gas turbine blade in hot gas path (turbine section) of power generation gas turbine. Occurrences of wear and crack were observed on gas turbine blades in this section. The blades are made of nickel base superalloy (GTD 111). Crack generally occurred at airfoil area of the blades while wear generally occurred at root area of the blades. The purpose of this study is to determine the degradation of two stages blades in the turbine section after being exposed to 24,000 running hours. The affected areas of the mating surfaces were analyzed through visual and microstructure testings and the type of degradation was discussed.