PSI- Issue 9

ScienceDirect Available online at www.sciencedirect.com Available o line at ww.sciencedire t.com Scie ceDirect Structural Integrity Procedia 00 (2016) 000 – 000 P o edi Structural Integr ty 9 (2018) 86–91 Available online at www.sciencedirect.com ScienceDirect Structural Int grity Procedia 00 (2018) 000–000 Available online at www.sciencedirect.com 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 Gruppo Italiano Frattura (IGF) ExCo. IGF Workshop “Fracture and Structural Integrity” Comparative investigation of mode I and II fracture toughness of dir ctly cured C RP and co-cured bonded CFRP joints F. Moroni a , A. Pirondi a, *, C. Pernechele b , A. Gaita b , L. Vescovi b a Dipartimento di Ingegneria e Architettura, Università di Parma, Parco Area delle Scienze, 181/A, 43124 Parma, Italy b Dallara Automobili, Via Provinciale, 33, 43040 Varano Melegari (PR), Italy Abstract Adhesive bonding is the elective joining system between Carbon-Fiber Reinforced Polymer (CFRP) parts because, with respect to fastening, it allows a large connection area, no additional parts (hence weight saving) and no need to drill holes into the composite, that is always detrimental for the strength due to the possibility of developing damage. However, the choice of bonding CFRP should be evaluated as alternative to direct curing in terms of strength and durability, compared to cost and manufacturing time and complexity. In this work, a comparison between directly cured and co-cured, bonded CFRP is done with respect to mode I and mode II fracture toughness, in order to understand whether bonding guarantees the same performance of a co-cured composite part. © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Gruppo Italiano Frattura (IGF) ExCo. Keywords: Carbon-Fiber Reinforced Polymer; bonded joints; fracture toughness 1. Introduction Th joi ing of composite laminates is generally mad by mechanical fastening or bonding, as testified from the large number of studies performed on the topic (Camanho and Tong, 2011; Vassilopoulos, 2015), while welding is confined to applications when composite matrix is of thermoplastic nature. Fastening ensures the possibility of decoupling and it is easier to inspect with respect to bonding, however it requires the drilling of a hole through the composite, as a result it generates fiber discontinuity, affecting bearing and shear strength of the component. On the IGF Workshop “Fracture and Structural Integrity” Comparative investigation of mode I and II fracture toughness of directly cured CFRP and co-cured bonded CFRP joints F. Moroni a , A. Pirondi a, *, C. Pernechele b , A. Gaita b , L. Vescovi a Dipartimento di Ingegneria e Architettura, Università di Parma, Parco Area del Scienze, 181/A, 43124 Parma, Italy b Dallara Automobili, Via Provinciale, 33, 43040 Varano Melegari (PR), Italy Abstract Adhesive bonding is the elective joining system between Carbon-Fiber Reinforced Polymer (CFRP) parts because, with res ect to fastening, it allows a large c nnection area, no additional parts (hence weight saving) nd no ne d to drill holes into the composite, t at is always detrimental for the strength due to the possibility of developing damage. How ver, the choice of bonding CFRP should be valuated as alternative to direct curing in terms of strength and dura ility, compared to cost and manufacturing time and complexity. In this work, a comparison between directly cured and co-cured, bond d CFRP is done with respect to mode I and mode II fracture toughness, in order to understand whether bonding guarantees the same performance of a co-cured composite part. © 2018 The Aut ors. Published by Elsevier B.V. Peer-review under responsibility of the Gruppo Italiano Frattura (IGF) ExCo. Keywords: Carbon-Fiber Reinforced Polymer; bo ed joints; fracture toughness 1. Introduction The joining of composite la inates is generally ade by mechanical fastening or bonding, as testified from the large numb r of studies performed on the topic (Camanho and Tong, 2011; Vassilopoulos, 2015), while welding is confined to applications when composite matrix is of thermoplastic nature. Fastening ensures the possibility of decoupling and it is easier to inspect with respect to bonding, however it requires the drilling of a hole through the composite, as a result it generates fiber discontinuity, affecting bearing and shear strength of the component. On the © 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 © 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 Gruppo Italiano Frattura (IGF) ExCo. 10.1016/j.prostr.2018.06.014 * Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt 2452 3216 © 2018 Th Authors. Published by Elsevier B.V. Peer-review under responsibility of the Gruppo Italiano Frattura (IGF) ExCo. 2452-3216 © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Gruppo Italiano Frattura (IGF) ExCo. * Corresponding author. Tel.: +39-0521-905885; fax: +39-0521-905705. E-mail address: alessandro.pirondi@unipr.it * Corresponding author. Tel.: +39-0521-905885; fax: +39-0521-905705. E-mail address: alessandro.pirondi@unipr.it