Abstract: Up to now, there are still no accurate and reliable methods for computing the stress field of a shrouded air-cooled turbine blade, because the cooled blade with a complex configuration works under high temperatures and great centrifugal loads, moreover, the distribution of aerodynamic loads is rather non-uniform. Usually, such problems occured in practice are tackled by means of experiments or statistics.In attempt to solve these problems, we applied the high order 3-dimensio-nal isoparametric elements for describing the complex configuration of blades. In order to solve the high order linear system of equations, we have used the frontal method with high accuracy and considerable economy of main memory space. The bicubic Coons interpolation function is also used to fit the space curved surface. For the sake of verifying the present method and the reliability of the given program, we have compared the results of numerical computations with those obtained from experiments on the revolution of the real blades at high speeds, and the comparison confirms the adaptability and the satisfactory accuracy of the present method.This method is available to various blades, such as solid or hollow blades; blades shrouded or unshrouded; blades with or without a shank root; and at high or normal temperatures.