A solving method is applied to conduct research on the non-linear thermal buckling behavior of local delamination near the surface of fiber-reinforced laminated cylindrical shell. The shape of delaminated region considered is elliptic, triangular and lemniscates. Young's modulus and the thermal expansion coefficient of material are treated as a function of temperature, which leads to the force in the middle plane of the sub-laminated shells a non-linear function of temperature. The critical temperatures of laminated cylindrical shells with various shaped local delamination, different stacking patterns and different radius of the laminated cylindrical shells are obtained by making use of the energy principle. It has been found that linear solution of the critical buckling temperature gives a higher value than that of non-linear consideration.