Gas turbine compressor blades are an integral component to a gas turbine assembly and their failures can lead to catastrophic downstream damage. The presence of a crack also leads to mode localization for all mode families, a phenomenon that cannot be captured by a single blade analysis. In the modal analysis study, increasing the depth of the crack leads to a decrease in the natural frequencies of both the single blade and bladed disk system, while increasing the rotational velocity increases the natural frequencies. Results demonstrate that for the applied loading condition, a mixed mode crack propagation is expected. In the fracture simulation, the influence of the size of a single edged crack as well as the rotational velocity on fracture parameters (stress intensity factors and J-Integral) are evaluated. Taking advantage of high performance computing resources, a high fidelity finite element model is considered in the parametric investigation. Once the crack front is perfectly defined and validated, a free vibration study is conducted by analyzing the natural frequencies and modeshapes for both a single blade and bladed disk system. The static fracture analysis is verified with a special purpose fracture code (FRANC3D). An open crack model is considered in the study and crack-tip driving parameters are estimated by using 3-D singular crack-tip elements in ANSYS \(\circledR \). This paper presents a methodology for conducting a 3-D static fracture analysis with applications to a gas turbine compressor blade.
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