PSI - Issue 13

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com Sci ceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structural Integrity 13 (2018) 2126–2131 ScienceDirect Structural Integrity Procedia 00 (2018) 000 – 000 ScienceDirect Structural Integrity Procedia 00 (2018) 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. © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. ECF22 - Loading and Environmental effects on Structural Integrity Peridynamic Modelling of Delamination in DCB Specimen U. Yolum a , E. Gök a , D. Coker b , M. A. Guler a a Dept. of Mechanical Engineering, TOBB University of Economics and Technology, Söğütözü, Ankara 06560 Turkey b Dept. of Aerospace Engineering, Middle East Technical University, Ankara, 06800 Turkey Abstract Peridynamics is a robust theory to capture failure initiation and failure propagation in both isotropic and orthotropic materials. This paper present a method to model Mod I delamination failure in composite materials using PD approach implemented in FEA. A bilinear PD damage law is formulated for PD interface by modifying the original failure formulation of Silling. That bilinear PD int rface behavior is inspired by the bilinear damage law of CZM mo els. A MATL B code is generated to generate PD interactions and corresponding surface correction factors. roposed formulation is adapted to FEA code ABAQUS. Using generated MATLAB pre-processing code, PD model of a DCB spe imen is gener t d. In addition, the same problem is solved using Cohesive Zone Modelling approach in ABAQUS. PD and FEA results are compared with results from literature. Obtained results indicate that PD solutions correlate well with CZM and results from literature. © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. Keywords: Peridynamic Theory; Failure; Composite Materials; DCB Test; Mode I N me clature PD ECF22 - Loading and Environmental effects on Structural Integrity Peridynamic Modelling of Delamination in DCB Specimen U. Yolum a , E. Gök a , D. Coker b , M. A. Guler a a Dept. of Mechanical Engineering, TOBB University of Economics and Technology, Söğütözü, Ankara 06560 Turkey b Dept. of Aerospace Engineering, Middle East Technic l University, Ankara, 06800 Turkey Abstract Peridynamics is a robust theory to capture failure initi tion and failure propagation in both isotropic and orthotropic materials. This paper pre ent a method to model Mod I delamin ti failure in com osite materials u ing PD ppr ach im le ented in FEA. A bilin ar PD damage law is formulated for PD inter ce by modifying the original failure formulation of Silling. That bilinear PD inte face behavior is in pired by the bilinear damage law of CZM mod ls. A MATLAB c de is generated to generate PD interactions nd corresponding surfac correction factors. Proposed formulation is adapted to FEA code ABAQUS. U ing generated MATLAB pre-pr cessing code, PD model of a DCB specimen is generated. In addition, the sam problem is solved using Cohesive Zone Modelling approach in ABAQUS. PD and FEA result are compared with results fro literature. Obtain results indicat that PD solutions cor elate well with CZM and results from lite ature. © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. Keywords: Peridynamic Theory; Failure; Composite Materials; DCB Test; Mode I Nomenclature PD Peridynamics FEA Finite Element Analysis F M Finite le ent Method CZ Cohesive Zone odelling Peridynamics FEA Finite Element Analysis FEM Finite Element Method CZM Cohesive Zone Modelling © 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.

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. * Corresponding author. Tel.: +90-312-292-4088; fax: +90312-292-4091. E-mail address: mguler@etu.edu.tr * Corresponding author. Tel.: +90-312-292-4088; fax: +90312-292-4091. E-mail ad ress: mguler@etu.edu.tr

* Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt

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.2018.12.197