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1. Introduction The aero gas turbine engine is the key technology of the aircraft; blade is one of the most important parts of the system. Vibration, especially resonance of the blade, will produce larger stress, which will lead to fatigue failure. Thus, the dynamic behavior of rotating blades has been studied by numerous researchers. Some simplified blade models such as beams, plates, and shells are used to investigate the vibration characteristics of the blades in the published literatures. Leissa and Jacob [1] investigated the free vibration of pretwisted, cantilevered beams and plates by using the Ritz method. The work was the first three-dimensional study of the problem. Yoo et al. [2] derived the equations of motion with a concentrated mass by using a modeling method with hybrid deformation variables and investigated the effects of the nondimensional parameters on the vibration characteristics of the pretwisted rotating blade through numerical analysis. Chandiramani et al. [3] simplified the pretwisted rotating blade as a laminated composite, hollow uniform box-beam model, which considers the centrifugal and Coriolis effects, transverse shear flexibility, and restrained warping, and studied the free and forced vibration by using HSDT and Galerkin method. Carrera et al. [4] used the Carrera unified formulation and FEM to study the free vibration analysis of rotating blades; the Coriolis and centrifugal force fields were included in their work. The beam models are quite suitable for blades with large aspect ratio and low width thickness ratio. However, flexible rotating structures such as blades with low aspect ratios are also widely used in actual engineering applications. Therefore, more and more literatures were found to study the vibration of blade with plate and shell models. Qatu and Leissa [5] were the first to study the effect of plate parameters such as twist angle, stacking sequence, and lamination angle on the natural frequency and mode shapes of laminated composite pretwisted cantilever plates by using the shallow shell theory and Ritz method. Nabi and Ganesan [6] analyzed the vibration characteristics of metal matrix composite pretwisted blades by using beam and plate theories, respectively, and summed up the quantitative comparison of natural frequency. Yoo and Chung [7] developed a linear dynamic modeling method for plates by using two in-plane stretch variables and analyzed and studied the transient characteristics of rotating plates. Hu et al. [8] proposed a numerical procedure for the free vibration analysis of pretwisted thin plates based on the thin shell theory and studied the vibration characteristics considering different twist rates and aspect ratios. Hashemi et al. [9] used the Mindlin plate theory and Kane dynamic method to develop a finite element formulation for vibration analysis of rotating thick plates. The coupling between in-plane and out-of-plane deformations and Coriolis effect was considered in the study. Sinha and Turner [10] derived the governing partial differential equation of motion for the rotating pretwisted plate by using the thin shell theory and studied the free vibration of a turbomachinery cantilevered airfoil blade with the Rayleigh–Ritz technique by considering the centrifugal force filed as a quasi-static load. Sun et al. [11] presented a dynamic model based on CLPT, investigated the vibration behavior of a rotating blade by using Hamilton’s principle, and studied the point and distribution forced response using a proportional damping model. 
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