RESEARCH ARTICLE


Failure Analysis for a Low Pressure Aeroengine Turbine Vane



Roberto Citarella1, *, Venanzio Giannella1, Edoardo Vivo2, Massimo Mazzeo2
1 Dept. of Industrial Engineering, via Giovanni Paolo II, 132, University of Salerno, Fisciano (SA), Italy
2 GE-Avio, Viale Giuseppe Luraghi, 20, Pomigliano d’Arco (NA), Italy


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© 2017 Citarella et al.

open-access license: This is an open access article distributed under the terms of the Creative Commons Attribution 4.0 International Public License (CC-BY 4.0), a copy of which is available at: https://creativecommons.org/licenses/by/4.0/legalcode. This license permits unrestricted use, distribution, and reproduction in any medium, provided the original author and source are credited.

* Address correspondence to this authors at the Dept. of Industrial Engineering, via Giovanni Paolo II, 132, University of Salerno, Fisciano (SA), Italy; Tel: +3908994111; E-mail: rcitarella@unisa.it


Abstract

Background & Objective

In this work, a thermo-mechanical fatigue application related to a fracture process simulation in a turbine vane is implemented, using a submodelling approach based on the principle of linear superposition.

Method

The proposed crack propagation approach leverages on a combined use of FEM and DBEM methodologies: the global analysis is solved by using FEM whereas the fracture problem is demanded to DBEM. In particular, a DBEM submodel is extracted from a global uncracked FE model and, in the new proposed formulation, boundary conditions are applied just on crack faces rather than loading subdomain boundaries with displacements/tractions and temperatures, as in the classical approach.

Results & Conclusion

The adopted approach solves the fracture problem by using simpler pure stress analyses rather than by thermal-stress analyses, as requested by the classical approach. Boundary conditions applied on the submodel crack faces come from the solution of a FE uncracked global model. The computational advantages of such alternative approach are highlighted and, in addition, a fatigue assessment is provided for a turbine vane, considering as initial crack the maximum design defect dictated by GE-Avio regulations for such kind of components.

Keywords: FEM-DBEM, Crack growth, Thermo-mechanical fatigue, Maximum design defect, Aeroengine turbine vane.