Fatigue Analysis For Aero Combustion Turbine Engine Blades

As an efficient power machine. gas turbine is widely used in many filed, especially in the aerospace field. The rotor blade is one of the most significant parts of aero gas turbine.because the rotor blade is always impacted by the high temperature gas. Worked in an terrible environment, turbine rotor blade is easily to be broken because of the stiffness, intensity.vibration and many factors. It may cause a catastrophe when the turbine rotor blade is broken.The damage ranges from halt of the machine to the disastrous accident. As a result, the analysis of fatigue is extremely essential.Firstly, this paper reviews the research achievements all over the world, which are about the analysis of the fatigue of the turbine rotor blade's intensity, and introduces the methods of fatigue analysis and working environment. After making the model of turbine rotor blade with the software-Pro/E. analyze the static force with ANSYS. According to the date calculating,centrifugal force, heat force resultant stress, we got the maximum distortion and force of the blade.Secondly, research the frequency and mode of vibration for five different speeds of ratating. With the help of looking up Campbell chart, we found the areas of resonance to avoid the rotating speed of the turbine, and the limit value of the force was found according to Goodman diagram.At last, we analyzed the fatigue life in the basis of static force analysis. We deduced the fatigue life of low cycle with applying Manson-Coffin equation and Miner theory. After that,we calculated the deflection of the blade model which in order to find the maxium value of the deflection, and got the fatigue life with the L-M equation. Total life of the turbine rotor blade can be calculated by Miner cumulative damage theory.