PSI - Issue 12

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at www.sciencedire t.com ScienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structural Integrity 12 8 71–81 Available online at www.sciencedirect.com ScienceDirect Structural Integrity 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. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/3.0/) Peer-review under responsibility of the Scientific Committee of AIAS 2018 International Conference on Stress Analysis. AIAS 2018 International Conference on Stress Analysis Numerical and experimental analysis of a composite rear spar subjected to random fatigue loading conditions A. Castriota a *, V. Dattoma a , B. Gambino b , R. Nobile a , F. Panella a , A. Pirinu a , A. Saponaro a a Università del Salento - Dipartimento di Ingegneria dell’Innovazione, Via per Monteroni, 73100 Lecce b Leonardo Aircraft SpA – Airframe, Structure Tech ologies, Zona ASI Incoronata – 81100 Foggia - Italia Abstract The work presents a numerical and experim ntal a alysis of a full-scale fatigue test on a CFRP rear spar of an aircraft solicited y a load history representative of variable load levels during the flight conditions. The structural element is essentially a double-T section with a hole and presents a repair by scarfing and hot bond process. The global stress field of the component was determined by a numerical model realized with a commercial FEM code. The numerical model is realized to reproduce the component geometry and stacking sequence, the representative constraints and service loads. The real component has been subjected to cyclic random fatigue stresses and subsequently a static bending load to evaluate the residual strength. Finally, the experimental results obtained, illustrated and discussed, were compared with the numerical ones. © 2018 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/3.0/) Peer-review under responsibility of the Scientific Committee of AIAS 2018 International Conference on Stress Analysis. Keywords: random fatigue test, rear spar, bending test, CFRP, FEM model. AIAS 2018 International Conference on Stress Analysis Numerical and experimental analysis of a composite rear spar ubjected to random fatigue loading conditions A. Castriota a *, V. Dattoma a , B. Gambino b , R. Nobile a , F. Panella a , A. Pirinu a , A. Saponaro a a Università del Salento - Dipartimento di Ingegneria dell’Innovazione, Via per Monteroni, 73100 Lecce b Leonardo Aircraft SpA – Airfra e, Structure Technologies, Zona ASI Incoronata – 81100 Foggia - Italia Abstract The work presents a numerical and experimental analysis of a full-scale fatigue test on a CFRP rear spar of an aircraft solicited by a load history representative of variable load levels during the flight conditions. The structural element is essentially a double-T section with a hole and presents a repair by scarfing and hot bond process. The global stress field of the component was determined by a numerical model realized with a commercial FEM code. The numerical model is realized to reproduce the component geo etry and stacking sequence, the representative constraints and service loads. The real component has been subjected to cyclic random fatigue stresses and subsequently a static bending load to evaluate the residual strength. Finally, the experimental results obtained, illustrated and discussed, were compared with the numerical ones. © 2018 The Authors. Published by Elsevier B.V. This is an open access article under th CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/3.0/) Peer-review under responsibility of the Scientific Committee of AIAS 2018 International Conf rence n Stress Analysis. Keywords: random f igue test, rear spar, bending t st, CFRP, FEM model. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. The main objective pursued in the aeronautical field is to minimize the non-paying weight. In recent decades, the development of composite materials has given a huge boost to development of the aeronautical sector but has also The main objective pursued in the aeronautical field is to minimize the non-paying weight. In recent decades, the development of composite materials has given a huge boost to development of the aeronautical sector but has also Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation. 1. Introduction 1. Introduction

* Corresponding author. Tel.: +39 0832 297786; fax: +39 0832 297768. E-mail address: alessandro.castriota@unisalento.it * Corresponding author. Tel.: +39 0832 297786; fax: +39 0832 297768. E-mail address: alessandro.castriota@unisalento.it

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. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/3.0/) Peer-review under responsibility of the Scientific Committee of AIAS 2018 International Conference on Stress Analysis. 10.1016/j.prostr.2018.11.105 * Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt 2452-3216 © 2018 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/3.0/) Peer-review under responsibility of the Scientific Committee of AIAS 2018 International Conference on Stress Analysis. 2452-3216 © 2018 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/3.0/) Peer-review u der responsibility of t Scientific ommittee of AIAS 2018 Internati al Conference on Stress Analysis.