PSI - Issue 2_A

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com ienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Struc ural Integrity 2 (2016) 3049–3056 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2016) 000–000 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2016) 000–000

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XV Portuguese Conference on Fracture, PCF 2016, 10-12 February 2016, Paço de Arcos, Portugal Thermo-mechanical modeling of a high pressure turbine blade of an airplane gas turbine engine P. Brandão a , V. Infante b , A.M. Deus c * a Department of Mechanical Engineering, Instituto Superior Técnico, Universidade de Lisboa, Av. Rovisco Pais, 1, 1049-001 Lisboa, Portugal b IDMEC, Department of Mechanical Engineering, Instituto Superior Técnico, Universidade de Lisboa, Av. Rovisco Pais, 1, 1049-001 Lisboa, Portugal c CeFEMA, Department of Mechanical Engineering, Instituto Superior Técnico, Universidade de Lisboa, Av. Rovisco Pais, 1, 1049-001 Lisboa, Portugal Abstract During their operation, modern aircraft engine components are subjected to increasingly demanding operating conditions, especially the high pressure turbine (HPT) blades. Such conditions cause these parts to undergo different types of time-dependent degradation, one of which is creep. A model using the finite element method (FEM) was developed, in order to be able to predict the creep behaviour of HPT blades. Flight data records (FDR) for a specific aircraft, provided by a commercial aviation company, were used to obtain thermal and mechanical data for three different flight cycles. In order to create the 3D model needed for the FEM analysis, a HPT blade scrap was scanned, and its chemical composition and material properties were obtained. The data that was gathered was fed into the FEM model and different simulations were run, first with a simplified 3D rectangular block shape, in order to better establish the model, and then with the real 3D mesh obtained from the blade scrap. The overall expected behaviour in terms of displacement was observed, in particular at the trailing edge of the blade. Therefore such a model can be useful in the goal of predicting turbine blade life, given a set of FDR data. 21st European Conference on Fracture, ECF21, 20-24 June 2016, Catania, Italy Fatigue test of an integrally stiffened panel: Prediction and crack growth monitoring using acoustic emission Lenka Michalcová a,  , Roman Růžek a a VZLU (Aerospace Research and Test Establishment), Beranovych 130, Prague-Letnany 199 05, Czech Republic Abstract Airworthiness regulations require operating advanced aircraft structures in compliance with a damage tolerance philosophy. Therefore, flight safety and structure reliability in service must be ensured using many types of additional activities, such as damage detection, crack growt prediction and critical size of cracks determ nation. As a result, the stru tur l health monitoring of aircrafts using various detection principles is needed. The paper documents the use of an acoustic emission method for the health monitoring of a typical airframe structure. It is represented by an integrally stiffened metallic panel demonstrating a bottom wing panel of a commuter aircraft. A fatigue test of the panel under a flight-by-flight loading sequence was performed. The crack growth was monitored by a visual method (VT) and an acoustic emission (AE) method. Several AE sensors placed in different configurations were used. AE reached very good agreement with the crack growth data, although the presented test was partially conducted in a noisy environment. The de-noised AE parameters were evaluated according to the actual position of the sensors and the crack tip. T e influence of stringers on the measured signal changes was stu ied as well. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. Keywords: Acoustic emission; crack growth; structure health monitoring; fatigue test Introduction The structural lements of an aircraft that carry all modes of applied loads are referred to as the primary structure. Different approaches have been developed over the years, beginning with the truss concept, followed by shell structures and alternatively sandwich structures. The shell concept utilizes sheet materials. These thin components shall be geometrically stiffened to avoid bulging in compression. There are two methods of manufacturing such structures. Stiffening elements may be added using either bonded joints or mechanically by rivets. The second 21st European Conference on Fracture, ECF21, 20-24 June 2016, Catania, Italy Fatigue test of an integrally stiffened panel: Prediction and crack growth monitoring using acoustic emission Lenka Michalcová a,  , Roman Růžek a a VZLU (Aerospace Research and Test Establishment), Beranovych 130, Prague-Letnany 199 05, Czech Republic Abstract Airworthiness regulations require operating advanced aircraft structures in compliance with a damage tolerance philosophy. Therefore, flight safety and structure reliability in servic must be ensured using many types of additional activities, such as damage detection, crack growth prediction and critical size of cracks determination. As a result, the structural health monitoring of aircrafts using various detection principles is needed. The pap r documents the use of an acoustic emission method for the health mo itori g of a typical airframe structure. It is represented by an integrally stiffened metallic panel demonstrating a bottom wing panel of a commuter aircraft. A fatigue test of the panel under a flight-by-flight l ading sequence was performed. The crack growth was monitored by a visual method (VT) and an acoustic emission (AE) method. Several AE s nsors placed in different c figurations were used. AE reached very good agreement with th crack growth data, although the presented test was partially conducted in a noisy environment. The de-noised AE parameters were evaluated according to the actual position of the sensors and th crack tip. The influenc of stringers on the measured signal changes w s studied as w ll. © 2016 The Autho s. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. Keywords: Acoustic emission; crack growth; structure health monitoring; fatigue test 1. Introduction The structural el ments of an aircraft that carry all modes of applied loads are referred to as the primary structure. Different approaches have been developed over the y ars, beginning with the truss concept, followed by shell structures and alternatively sandwich struct res. The shell concept utilizes sheet mat rials. These thin components shall be geometrically stiffened to avoid bulging in compression. There are two methods of manufacturing such structures. Stiffening elements may be added using either bonded joints or mechanically by rivets. The second Copyright © 2016 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/). Peer-review under responsibility of the Scientific Committee of ECF21. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation. 1.

2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Copyright © 2016 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license ( http://creativecommons.org/licenses/by-nc-nd/4.0/ ). Peer review under responsibility of the Scientific Committee of ECF21. 10.1016/j.prostr.2016.06.381 2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. 2452 3216 © 2016 Th Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. * Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt * Lenka Michalcová. Tel.: +420-225-115-409; fax: +420-225-115-300. E-mail address: michalcova@vzlu.cz * Lenka Michalcová. Tel.: +420-225-115-409; fax: +420-225-115-300. E-mail address: michalcova@vzlu.cz