Low cycle fatigue numerical estimation of a high pressure turbine disc for the AL-31F jet engine
1 Technical University of Kosice, Department of Aviation Engineering, 7 Rampová, 04221 Košice, Slovakia
2 University of West Bohemia, Department of Power System Engineering, 22 Univerzitní, 30614 Pilsen, Czech Republic
* Corresponding author: email@example.com
Published online: 12 May 2017
This article deals with the description of an approximate numerical estimation approach of a low cycle fatigue of a high pressure turbine disc for the AL-31F turbofan jet engine. The numerical estimation is based on the finite element method carried out in the SolidWorks software. The low cycle fatigue assessment of a high pressure turbine disc was carried out on the basis of dimensional, shape and material disc characteristics, which are available for the particular high pressure engine turbine. The method described here enables relatively fast setting of economically feasible low cycle fatigue of the assessed high pressure turbine disc using a commercially available software. The numerical estimation of accuracy of a low cycle fatigue depends on the accuracy of required input data for the particular investigated object.
© The Authors, published by EDP Sciences, 2017
This is an Open Access article distributed under the terms of the Creative Commons Attribution License 4.0, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.