Damage analysis of directionally solidified turbine blade after service exposure in aero-engine
In this paper, the turbine blade was made of a nickel-base alloy DZ125 and the acro-engine has been in service for first overhaul of life cycle.The investigation was started with a thorough visual inspection of the blade surfaces, by visual inspection, we found that there was wear damage on the tip of the blade, accompanied by surface changes in colour as well as in roughness.During the hardness test, we found that the hardness of the test point changes little in the airfoil of the blade.Followed by analytical simulation, the main factors lead to degradations in turbine blade arc centrifugal force and high temperature environment.With the aid of the analytical simulation parallel to the finitc element method, we finally get the highest temperature area and biggest radial stress area in turbine blade, which could give clear instructions in determining the key position for metallurgical examinations.Time dependent degradation for 1st stage microstructure changes by position in the blade.In the metallurgical analysis, the raftingγphase, MC decomposition formation occurred and progressed with increasing service time.Compared with joint parts in turbine blade, microstructure changes differently in different area of the blade.The microstructure in leading edge and trailing edge area where suffered from highest temperature degrades badly.This agrees well with the FEM results.This new inspection method has a certain guiding significance for the overhaul of the blade inspection work.
turbine blade overhaul degradation analytical simulation microstructure changes nickel-base superalloy
Yang XG Huang WQ Shi DQ
School of Energy and Power Engineering, Beihang University, Beijing 100191, China School of Energy and Power Engineering, Beihang University, Beijing 100191, China;The Collaborative
国际会议
长沙
英文
177-181
2016-10-16（万方平台首次上网日期，不代表论文的发表时间）