Dynamic stress analysis of rotating turbo-machinery bladed-disk systems

Abstract

The steady state dynamic stress and deformation analysis of high pressure stage turbomachinery bladed-disks is carried out taking into account all the geometric complexities involved. The contributions due to initial stress and membrane behaviour are included. Only one substructure is used for finite element modelling and analysis, taking advantage of rotational periodicity. A triangular shell element with six degrees of freedom per node is employed for this purpose. The blade and disk attachment is established by a set of constraint equations obtained by the Love-Kirchhoff hypothesis. The final set of equations are solved by an out of core submatrices elimination method. The influence of different levels of approximations and various geometric parameters on the stresses and deformations is discussed.