PSI - Issue 2_B

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 Struc ural Integrity 2 (2016) 2222–2229 Available online at www.sciencedirect.com ScienceDire t 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 Study on microscopic ductile fracture of in-sit TiB 2 /2024 Al matrix composite Su Jie, Li Yazhi*, Jiang Wei, Zhang Dailong School of Aeronautics, Northwestern Polytechnical University, 127 West Youyi Road, Xi'an 710072, China Abstract The microscopic fracture behavior, or in detail, damage initiation, growth and coalescence of in-situ TiB 2 particle reinforced 2024-T4 Al matrix composit (in-situ PRAMC) synthesized through an exothermic reaction process is investigated via in situ scanning electron microscopy (SEM) test with tensile load. Brittle fracture of large particles and clusters of small particles are identified in the early stage. The number of micro cracks accumulates with the increase of tension load. The debonding at the interface of large particle or cluster of small particles with Al matrix is scarcely found, which ensure an effective load transfer from particles into ductile matrix. The coalescence of micro cracks leads to final fracture. The fracture morphology observation confirms the feature of ductile fracture. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. Keywords: microscopic fracture behavior, cluster of small particles, micro cracks, fracture morphology observation 1. Introduction Particle reinforced Al matrix compos tes (PRAMCs) have b en applied in m ny fields such as aviation, spaceflight and automobile industry. Compared to their Al matrix, PRAMCs commonly have better performances, such as higher specific strength, higher specific modulus, better fatigue property, higher damping and wear resistance etc (Clyne 1995; Chawla 2006). But their applications are partly limited due to the decreased ductility and fracture toughness (Akbari 2015). Therefore the fracture mechanisms of PRAMCs have attracted more and more research effort. The mechanical properties and damage mechanisms of PRAMCs strongly depend on their synthetization technologies. There are mainly two preparation methods for PRAMCs according to particle adding manners, 21st European Conference on Fracture, ECF21, 20-24 June 2016, Catania, Italy Study on microscopic ductile fracture of in-situ TiB 2 /2024 Al matrix composite Su Jie, Li Yazhi*, Jiang Wei, Zhang Dailong School of Aeronautics, Northwestern Polytechnical University, 127 West Youyi Road, Xi'an 710072, China Abstract The microscopic fracture behavior, or in detail, damage initiation, growth and coalescence of in-situ TiB 2 particle reinforced 2024-T4 Al matrix composite (in-situ PRAMC) synthesized through an exothermic r a tion process is investigated via in situ scanning electron microscopy (SEM) test with tensile load. Brittle fracture f large particles and clusters of sm ll particles are ide tified in the early stage. The number of micro cracks accumulates with the incre se of tension load. The debonding at th nterfac of large p rticle or cluster of small part les with Al matrix is scarcely fou d, which ensure an effective load transfer from particles into ductile matrix. The coale cence of micro cracks le ds to fin l fracture. The fracture morphology observatio confirms the feature f ctile fr cture. © 2016 The Authors. Published by Elsevier B.V. Peer-review under espons bility of the Scientific Committee of ECF21. Keywords: microscopic fracture behavior, cluster of small particles, micro cracks, fracture morphology observation 1. In roduction Pa ticl r inforc d Al matrix composites (PRAMCs) have bee applied in many fields such as avi tion, spaceflight and utomob le industry. Compared to th ir Al matrix, PRAMCs commonly have better performances, such s higher specific strength, higher specific modulus, better fatigue property, higher damping and wear resistance etc (Clyne 1995; Chawla 2006). But the r applications are partly limited due to t e decreased ductility and fracture toughness (Akbari 2015). Therefore the f acture mechanisms of PRAMCs have a tract d more and more resea ch effort. The mechanical properties and damage mechanisms of PRAMCs strongly depend on their synthetization technologi s. There are mainly two preparation methods or PRAMC according to particle adding manners, 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.

* 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 ECF21. * Corresponding author. Tel.: +86-29-88460621; fax: +86-29-88460621. E-mail address: yazhi.li@nwpu.edu.cn 2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. * Corresponding author. Tel.: +86-29-88460621; fax: +86-29-88460621. E-mail address: yazhi.li@nwpu.edu.cn

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.2016.06.278