PSI - Issue 13

ScienceDirect Available online at www.sciencedirect.com Available online at www.sciencedire t.com ScienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structural Integrity 13 (2018) 1014–1 19 Available online at www.sciencedirect.com ScienceDirect StructuralIntegrity Procedia 00 (2018) 000 – 000 Available online at www.sciencedirect.com ScienceDirect StructuralIntegrity 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. ECF22 - Loading and Environmental effects on Structural Integrity Numerical modeling of 3D woven hybrid composites for stiffness and strength prediction Ahmed Sohail*, Zheng Xitao, Shiekh Muhammad Zakir, Zhang Di School of Aeronautics, Northwestern Polytechnical University, Xi’an PR China Due to recent development of the advanced 3D woven composites, it has been possible to adjust the mechanical properties either by placing the fiber tows in a certain direction or by replacing the fibers having nominal mechanical properties with the fiber of higher mechanical properties in a certain proportion. The later process is known as hybridization of reinforcement material. By adding the fibers with higher mechanical properties adds the cost and second and more important is the estimation of elastic and strength properties of hybridized material. In the current study, an efficient numerical model is established which can estimate the in-plane elastic and strength properties of 3D hybrid woven composites. At first a detailed geometry is constructed for a finite element mosaic model for a weave configuration which is already available in the literature. After validating the models successfully, fiber tows in a certain ratio are replaced with other materials to attain the hybridization of 3D woven composite. Finally, a numerical model established to find the elastic and strength properties of hybrid 3D woven composite © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. Keywords: 3D woven composites; hybridization; elastic properties; strength; numerical modeling 1. Introduction Delamination can be characteriz d as one of the major failure mechanisms in the employment of laminated composite materials, Wang et al. (1985). Different through thickness reinforcement can be introduced to avoid such kind of failure mechanisms. 3D weaving technique is one of the ways where a z-yarn is used to bind the weft and warp fiber tows together to make one pre-form, Stobbe and Mohammad (2003). The architecture of 3D woven composite © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 or anizers. ECF22 - Loading and Environmental effects on Structural Integrity Numerical modeling of 3D woven hybrid composites for stiffness and strength prediction Ahmed Sohail*, Zheng Xitao, Shiekh Muhammad Zakir, Zhang Di School of Aeronautics, Northwestern Polytechnical University, Xi’an PR China Abstract Due to recent development of the advanced 3D woven composites, it has been possible to adjust the mechanical properties either by placing the fib r tows in a cert in direction or by replacing the fiber having nominal mechanical properties with the fiber of higher mechanical properties in a certain pr portion. The later process is known as hybridization of reinforc ment material. By adding the fibers with high r mech nical pro erties adds the cost and second and more important is th estimatio of elastic and strength properties of hybridized m teri l. In the current study, an effici nt umerical model is established which can estimate the in-plane elastic and strength properties of 3D hybrid woven composites. At first a detail d g ometry is constru ted for a finit eleme t mosaic model for a weave configuration which is already available in the literature. After validating the models succ ssfully, fiber tows in a certain ratio are eplaced with othe materials to attain the hybridization of 3D woven comp site. Finally, a numerical model established to find the elastic and strength properties of hybrid 3D woven composite © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. Keywords: 3D woven composites; hybridization; elastic properties; strength; numerical modeling 1. Introduction Delamination can be characterized as one of the major failure mechanisms in the employment of laminated composite materials, Wang et al. (1985). Different through thickness reinforce ent can be intr duced t avoid such kind of failure mechanisms. 3D weaving technique is one of t e ways where a z-yarn is used to bind the weft an warp fiber tows together to make one pre-form, Stobbe and Mohammad (2003). The architecture of 3D woven composite © 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. Abstract

* Corresponding author. Tel.: +0086-15691970571. E-mail address: s.ahmed@mail.nwpu.edu.cn * Corresponding author. Tel.: +0086-15691970571. E-mail ad ress: s.a med@mail.nwpu.edu.cn

* 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 responsibility 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.2018.12.189