Metodología para simulación de fenómenos de perforación en placas debidos a fallas del tipo no contenida de turbinas de avión

Abstract

ABSTRACT: In this Project a Methodology is developed by using the finite element method (FEA), to simulate impact of debris from rotating parts that fail during operation of an aircraft engine uncontained by the engine case. One of the critical cases is where the debris hits the aircraft fuselage, because of passenger and aircraft safety. The methodology proposed here is based on the work by Norman F. Knight Jr: Penetration simulation for uncontained engine debris impact on fuselage-like panels using LS-DYNA. However, the tools used for the analysis were different. In the one hand, the aforementioned paper shows some guidelines to perform the simulation but details are not shown. This thesis results were validated by comparing them to Knight´s results, and the available experimental data. In this Project a Methodology is developed by using the finite element method (FEA), to simulate impact of debris from rotating parts the failed during operation of an aircraft engine and its case was not able to contain. One of the critical cases is where the debris hits the aircraft fuselage, because in one hand it affects the aircraft´ airworthiness and in the other people could be hurt or even death. To get the methodology proposed here, a former project was uses as base, it was the paper “Penetration simulation for uncontained engine debris impact on fuselage-like panels using LS-DYNA” written by Norman E. Knight. Which is the same event simulated in this project, however the tools used for the analysis where different. In the other hand the aforementioned paper shows some guidelines to perform the simulation but details are not shown. The present project validates the results the same way Norman F. Knight did, with the experimental data showed in the paper.

RESUMEN: En este trabajo se desarrolló una metodología con el Método del Elemento Finito (MEF) para simular eventos de impacto de fragmentos de partes rotativas que fallaron durante la operación de una turbina de avión, y que la carcasa de la misma no fue capaz de contener. Uno de los casos críticos ocurre cuando el impacto de tales fragmentos se da en el fuselaje del avión, ya que en este caso, se pone en riesgo la seguridad de pasajeros y aeronave. La metodología producto de esta tesis, está basada principalmente en el artículo Simulación de la penetración debido al impacto de fragmentos debidos a una falla no contenida en los paneles de un fuselaje usando LS-DYNA, de Norman F. Knight Jr, el cual hace la simulación del mismo evento que se desarrolla aquí; sin embargo, las herramientas utilizadas para el análisis son diferentes. Por otro lado, el artículo mencionado contiene unas guías de cómo hacer la simulación, pero no lo explica en detalle. Los resultados de la metodología expuesta en esta tesis se validaron utilizando los resultados del artículo de Knight y los resultados experimentales disponibles.