The Turbine Engine Blades Stress-Strain State Under the Vibration Load

Abstract

The problem of turbine engines blades stress-strain state has been studied. All calculations have been provided for the cooled blades constructions, used in the turbo machinery manufacturing. The investigation’s purpose was to develop the new adaptive mathematical model of turbine engine bladed disks with circular damping links stress-strain state by means of finite elements method. The foregoing approach to the finite elements method was borrowed from the literature on finite elements method. The main mathematical models and some types of the finite elements can’t be used for the correct description of the foregoing problem. The matter is that turbine blades have constructional non-homogeneity, which hardly ever could be correctly explained, using well-known finite elements and their mathematical dependences. On the other hand the variable aerodynamic force influence has also been taken into consideration. That is why the new model, which consists of sections, including disk’s sector, the whole blade and parts of damping links, has been developed. The finite elements methodology has been used for the dynamic stresses of this section calculation. Such approach gives an opportunity to describe the stress-strain state of the whole bladed disk as the superposition of the developed sections

Gas Turbine Engines Impellers Forced Vibration and Stress-Strain State Investigation

“…The damper links, connecting the blades in a unity were modeled using a rod finite element. The disk model included 230 first-order hexagonal finite elements with 1254 degrees of freedom totally [9]. To study the impeller forced vibration amplitudes and frequencies let's use the Lagrange variation principle.…”