PSI - Issue 2_B

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ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com Sci nceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 2 (2016) 158–165 Available online at www.sciencedirect.com Structural Integrity Procedia 00 (2016) 000–000 Available online at www.sciencedirect.com Structural Integrity Procedia 00 (2016) 000–000 0

www.elsevier.com/locate/procedia www.elsevier.com / locate / procedia www.elsevier.com / locate / procedia www.e .

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.2016.06.021 ∗ Corresponding author. Tel.: + 43-732-2468-6663 ; fax: + 43-732-2468-6662. E-mail address: susanne . hoerrmann@jku.at 2452-3216 c 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. With the increased use of carbon fiber reinforced polymers (CFRP), e.g. in the automotive industry, the demand for e ffi cient manufacturing of large integrated structures with short cycle times is growing. One solution is the use of non-crimp fabrics (NCF), which are as easy to ha dle as weaves wit better in-plane material properties due t aligned fibers and high-pressure resin transfer moulding (HP-RTM). With HP-RTM a reduction of the cycle time to less than 10 min can be reached by application of pressures from 30 to 120 bar inside the molds (Gardiner (2015)). Im- ∗ Corresponding author. Tel.: + 43-732-2468-6663 ; fax: + 43-732-2468-6662. E-mail address: susanne . hoerrmann@jku.at 2452-3216 c 2016 The Auth rs. Publi hed by Elsevier B.V. e r-review under responsibil ty of the Scientific Committee of ECF21. o m a n h l s . . . mail dd anne . hoer mann@jku.at . . . . * Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt With the increased use of carbon fiber reinforced polymers (CFRP), e.g. in the automotive industry, the demand for e ffi cient manufacturing of large integrated structures with short cycle times is growing. One solution is the use of non-crimp fabrics (NCF), which are as easy to handle as weaves with better in-plane material properties due to aligned fibers and high-pressure resin transfer moulding (HP-RTM). With HP-RTM a reduction of the cycle time to less than 10 min can be reached by application of pressures from 30 to 120 bar inside the molds (Gardiner (2015)). Im- 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. Copyright © 2016 The Authors. Published y Elsevier B.V. T is is an ope acc ss article und r the CC BY-NC-ND license (http://creativ ommons.org/licenses/by-nc-nd/4.0/). Peer-review und r responsibility of the Scientific Committe of ECF21. 21st European Conference on Fracture, ECF21, 20-24 June 2016, Catania, Italy Through-thickness fatigue behavior of non-crimp fabrics featuring manufacturing defects Susanne Ho¨ rrmann a,b, ∗ , Adi Adumitroaie b , Martin Schagerl a,b a CD-Lab Structural Strength Control of Lightweight Constructions, Johannes Kepler University Linz, Altenberger Straße 69, 4040 Linz, Austria b Institute of Constructional Lightweight Design, Johannes Kepler University Linz, Altenberger Straße 69, 4040 Linz, Austria Abstract The use of cost e ffi cient CFRP materials is growing especially in the automotive applications. Here, a challenge is delamination occurring during service. Out-of-plane loading should be avoided in composite structures, since it is the weakest loading direction. However, this is not always possible in mor complex geom tries or at joints. Henc , there is a demand for through-thickness fatigue properties, for design and analysis of CFRP structures. Fatigue damage is often initiated by manufacturing imperfections or defects, such as voids, in-plane or out-of-plane ply waviness or folds of plies. In this research work, the influence of a fold defect on the through-thickness mode I fatigue fracture behavior of an automotive non-crimp fabric laminate is assessed, through the means of both experimental testing and numerical simulation. The selected test method is the direct through-thickness tensile load application. This method allows microscopic analysis of the fract re surfaces of the dela inated specimens, which contributes to a better understanding of the influence the manufacturing defect has on the damage behavior and material performances. Fractography shows, that interlaminar fracture is predominant due to stitching yarn concentration and resin rich areas. A knock down of 10 % due to the presence of the fold defect is observed and can be further fed back into the fatigue material properties for simulation and analysis of structural composite parts. In this way, the presence of defects can be quantified and accounted for during the design stage. c 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. Keywords: Manufacturing defects, CFRP, through-thickness loading, fatigue damage; 21st European Conference on Fracture, ECF21, 20-24 June 2016, Catania, Italy Through-thickness fatigue behavior of non-crimp fabrics featuring manufacturing defects Susanne Ho¨ rrmann a,b, ∗ , Adi Adumitroaie b , Martin Schagerl a,b a CD-Lab Structural Strength Control of Lightweight Constructions, Johannes Kepler University Linz, Altenberger Straße 69, 4040 Linz, Austria b Institute of Constructional Lightweight Design, Johannes Kepler University Linz, Altenberger Straße 69, 4040 Linz, Austria Abstract The use of cost e ffi cient CFRP materials is growing especially in the automotive applications. Here, a challenge is delamination occurring during service. Out-of-plane loading should be avoided in composite structures, since it is the weakest loading direction. However, this is not always possible in more complex geometries or at joints. Hence, there is a demand for through-thickness fatigue properties, for design and analysis of CFRP structures. Fatigue damage is often initiated by manufacturing imperfections or defects, such as voids, in-plane or out-of-plane ply waviness or folds of plies. In this research work, the influence of a fold defect on the through-thickness mode I fatigue fracture behavior of an automotive non-crimp fabric laminate is assessed, through the means of both experimental testing and numerical simulation. The selected test method is the direct through-thickness tensile load application. This method allows microscopic analysis of the fracture surfaces of the delaminated specimens, which contributes to a better understanding of the influence the manufacturing defect has on the damage behavior and material performances. Fractography shows, that interlaminar fracture is predominant due to stitching yarn concentration and resin rich areas. A knock down of 10 % due to the presence of the fold defect is observed and can be further fed back into the fatigue material properties for simulation and analysis of structural composite parts. In this way, the presence of defects can be quantified and accounted for during the design stage. c 2016 The Authors. Published by Elsevier B.V. P review unde responsibility of the Scientific Committee of ECF21. Keywords: Manufacturing defects, CFRP, through-thickness loading, fatigue damage; o b rti a,b , , , , titu of Constructional Lightweight Design, Johannes Kepler University Linz, Altenberger Straße 69, 4040 Lin , Austria T e ffi o H e e e f . a T m f f e f o K , , , © 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. Introduction 1. Introduction 1. Introduction