Failure Analysis for a Low Pressure Aeroengine Turbine Vane


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.

Cite this paper

@inproceedings{Citarella2017FailureAF, title={Failure Analysis for a Low Pressure Aeroengine Turbine Vane}, author={R. Citarella and Venanzio Giannella and Edoardo Vivo and Massimo Mazzeo}, year={2017} }