PSI - Issue 8

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at www.sciencedire t.com cienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 8 (2018) 137–153 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2017) 000–000 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2017) 000–000

www.elsevier.com/locate/procedia www.elsevier.com/locate/procedia

www.elsevier.com/locate/procedia

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. Copyright © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of AIAS 2017 International Conference on Stress Analysis AIAS 2017 International Conference on Stress Analysis, AIAS 2017, 6-9 September 2017, Pisa, Italy Numerical FEM Evaluation for the Structural Behaviour of a Hybrid (bonded/bolted) Single-lap Composite Joint E. Armentani a *, M. Laiso b , F. Caputo b , R. Sepe a a Dept. of Chemical, Materials and Production Engineering, University of Naples Federico II, P.le V. Tecchio 80, 80125 Naples, Italy b Dept. of Industrial and Information Engineering, Università della Campania “Luigi Vanvitelli”, Via Roma 29, 81031 Aversa, Italy Abstract The structural behaviour of a single-lap hybrid (bonded/bolted) composite joint subjected to a tensile external load was evaluated by m ans of the Finite Element Method (FEM). In particular, the distribution of stres es acting in its adhesive layer was compared with that relative to the case of a simply adhesive bonded joint. Furthermore, the load transferred by the bolt was determined at different characteristics of the adhesive and of the applied external tensile load, corresponding to both single and double bolt configuration. The obtained values were in turn compared with experimental data found in literature, so validating the produced numerical simulations. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of AIAS 2017 International Conference on Stress Analysis. Keywords: hybrid joint; composites; FEM; ANSYS®; adhesive; bonded; bolted; HI-LOK TM ; Drucker-Prager yield criterion 1. Introduction In many industrial sectors, particularly ae ospace, dev lop a d use of composite materials is very relevant. These materials allow the production of goods relatively complex and of big dimensions, the use of joints results to be always necessary for creating complex structures. Traditionally joints between composite materials were made by a mechanical fastening, however this technique shows various disadvantages such as high stress concentrations at the AIAS 2017 International Conference on Stress Analysis, AIAS 2017, 6-9 September 2017, Pisa, Italy Numerical FEM Evaluation for the Structural Behaviour of a Hybrid (bonded/bolted) Single-lap Composite Joint E. Armentani a *, M. Laiso b , F. Caputo b , R. Sepe a a ept. of Chemical, Materials and Production Engineering, University of Naples Federico II, P.le . Tecchio 80, 8 125 Naples, Italy b Dept. of Industrial and Information Engineering, Università della Campania “Luigi Vanvitelli”, Via Roma 29, 81031 Aversa, Italy Abstract The structural behaviour of a single-lap hybrid (bonded/bolted) composite joint subjected to a tensile external load was evaluated by means of the Finite Element Method (FEM). In particular, th distribution of str sses acting in its a hesive layer compared with that relative to the ase of a simply adhesive bonded joint. Furth rmore, the l ad transferred by the bolt was etermined at different characteristics of the adhesive and of the applied external tensile load, c rresponding to both single a d dou le bol configuration. The btained values were in turn compared with experimental data found in literature, so validating the produced numerical simulations. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of AIAS 2017 International Conference on Stress Analysis. Keywords: hybrid joint; composites; FEM; ANSYS®; adhesive; bonded; bolted; HI-LOK TM ; Drucker-Prager yield criterion 1. Introduction In many industrial sectors, particularly aerospace, develop and use of co posite materials is very relevant. These materials allow t e production of goods relatively complex and of big dimensions, the use of joints results to be always necessary for creating complex structures. Traditionally joints between composite materials were made by a mechanical fastening, however this technique shows various disadvantages such as high stress concentrations at 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.

* Corresponding author. Tel.: +39-081-768-24-50; fax: +39-081-768-24-52. E-mail address: enrico.armentani@unina.it * Correspon ing author. Tel.: +39-081-768-24-50; fax: +39-081-768-24-52. E-mail address: enrico.armentani@unina.it

2452-3216 © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of AIAS 2017 International Conference on Stress Analysis. 2452 3216 © 2017 Th Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of AIAS 2017 International Conference on Stress Analysis.

* 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 Copyright  2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of AIAS 2017 International Conference on Stress Analysis 10.1016/j.prostr.2017.12.015