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Characteristics of non-stationary thermal stresses in the disc of the last turbine stage

In the paper “Modelling of Non-stationary Thermal Stresses in Steam Turbine Rotors” [1] presented on TMT 2004, the algorithm and the results of non-stationary thermal stresses modelling in steam turbine rotor by means of the users software package are shown. Non-stationary thermal stresses are stipulated by pressure change on turbine exit. The results of non-stationary thermal stresses calculations (i.e. of modelling) show on several characteristic regions of the rotor thermal stressed state: a) the rotor central bore; b) the low-pressure rotor; c) the disc of the last turbine stage, and d) the rear-end labyrinth gland. Due to in the paper “Characteristics of Non-Stationary Thermal Stresses in Steam Turbine Rotors” [2] presented on TMT 2006, these characteristic regions are additionally analysed. As in the disc of the last turbine stage the high gradients of thermal and mechanical quantities (temperature, heat flux, deformation, stress) are determined, so this region of rotor is analysed in detail. In this paper the results of this analyse are presented.