PSI - Issue 13

ScienceDirect Available online at www.sciencedirect.com Available online at ww.sciencedire t.com Sci ceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structural Integrity 13 (2018) 1442–1446 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2018) 000–000 Available online at www.sciencedirect.com ScienceDirect Structural I t grity Procedia 00 (2018) 000–000

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ECF22 - Loading and Environmental effects on Structural Integrity ECF22 - Loading and Environmental effects on Structural Integrity

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. Fracture behaviour of prepreg laminates studied by in-situ SEM mechanical tests Simon Bard a , Martin Demleitner a , Markus Häublein a , Volker Altstädt a * a University of Bayreuth, Polymer Engineering, Universitätsstr. 30, 95444 Bayreuth, Germany Abstract By using a miniature testing device placed in a Scanning El ctron Mi roscop (SEM) it was possible to investigate the fracture toughness in mode I of graphite modified prepreg laminates. Different tools have been developed to expand the possibilities of the commercially available tool. In-situ deformation studies can thereby be used to evaluate the crack behavior of carbon fiber reinforced composites (CFRP). The matrix of the CFRP has been optimized for higher thermal and electrical conductivity to be used in electrically driven aircrafts. The crack propagates through the matrix and shows crack deviation at the graphite particles, which could be shown in in-situ SEM mechanical tests. Also the toughening mechanism of thermoplastic interleaved laminates have been investigated in the SEM mechanical tests. A crack transition between different layers was clearly visible in SEM. © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. Keywords: SEM; Carbon Fiber; CFRP; fracture toughness, Mode I fracture toughness © 2018 The Authors. Published by Els vier B.V. Peer-revi w under responsibility of the ECF22 or anizers. Fracture behaviour of prepreg laminates studied by in-situ SEM mechanical tests Simon Bard a , Martin Demleitner a , Markus Häublein a , Volker Altstädt a * a University of Bayreuth, Polymer Engineering, Universitätsstr. 30, 95444 Bayreuth, Germany Abstract By using a miniature testing device placed in a Scanning Electr n Microscope (SEM) it was possible to investigate the fracture toughness in mode I of graphite modified prepreg laminates. Different to ls have been veloped to expand th possibilities of th commercially available tool. In-situ deformation studies can thereby be used to evaluate the crack behavior of carbon fiber reinforced composites (CFRP). The matrix of the CFRP has been optimized for higher thermal and electrical conductivity to be used in electrically driven aircrafts. The crack propagates through the matrix and shows crack deviation at the graphite particles, which could be shown in in-situ SEM mechanical tests. Als the toughening mec anism of thermoplastic interleaved laminates have been investigated i the SEM mechanic l tests. A crack transition b tween different layers was clearly visible in SEM. © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. Keywords: SEM; Carbon Fiber; CFRP; fracture toughness, Mode I fracture toughness

Nomenclature DIC N menclature DIC GI

Digital Image Correlation

© 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Digital Image Corr lation Strain ene gy release rate mode I Strain energy release rate mode I Interlaminar Shear Strength Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation. Scanning Electron Microscope GIC ILSS SEM ILSS SEM Interlaminar Shear Strength Scanning Electron Microscope

* Corresponding author. Tel.: +49 (0) 921 55 7476; fax: +49 (0) 921 55 7473. E-mail address: simon.bard@uni-bayreuth.de * Corresponding author. Tel.: +49 (0) 921 55 7476; fax: +49 (0) 921 55 7473. E-mail ad ress: sim n.bard@uni-bayreuth.de

* Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt 2452-3216 © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. 2452-3216 © 2018 The Authors. Published by Elsevier B.V. Peer review under r sponsibility of the ECF22 organizers.

2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016.

2452-3216  2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. 10.1016/j.prostr.2018.12.299