PSI - Issue 8

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 Structu al Integrity 8 (2018) 444–451 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

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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. 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 Mechanical behaviour of composite material in presence of wrinkles V. Dattoma a , B. Gambino b , R. Nobile a* , F.W. Panella a a Università del Salento - Dipartimento di Ingegneria dell’Innovazione, Via per Monteroni, 73100 Lecce - Italia b Leonardo Aircraft SpA – Airframe, Structure Technologies, Zona ASI Incoronata – 81100 Foggia - Italia Abstract In this work the mechanical behaviour of CFRP laminates having an artificial wrinkle introduced in the critical section has been studied in the Open Hole Tension and Open Hole Compression configuration. The experimental test allowed determining the failure mechanism and the knockdown of the ultimate strength in five different configurations. © 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: Composite material; CFRP; Wrinkles; Mechanical behaviour 1. Introduction In the last y ar the diffusion of composite l minates for structural applications is co tinuously growing and the exp ri nce highlighted dvant ges and criti al point of this kind of material. An aware use of these mat rials requires a critical evaluation of the effects that the presence of imperfections or defects introduced during manufacturing could provoke on the mechanical behavior and structural performance. Several geometrical irregularities are originated by the difficulty that an operator encounter during placement of fiber or laminate during manufacturing, as reported in Cantwell and Morton (1992). They consist in lack of planarity of plies, introduction of undulations, partial superposition or wrinkles. In all cases, the real orientation of fibers may diff r highly from the one defined in design phase, leading to unexpected stress concentration. In particular, a recurrent and diffused imperfection is represented by wrinkles. A large number of mechanisms are involved in the AIAS 2017 International Conference on Stress Analysis, AIAS 2017, 6-9 September 2017, Pisa, Italy Mechanical behaviour of omposite material in presence of wrinkles V. Dattoma a , B. Gambino b , R. Nobile a* , F.W. Panella a a Università del Salen o - Dipartimento di Ingegneria del ’Innovazione, Via pe Monteroni, 73100 Lecce - It lia b Leonardo Aircraft SpA – Airframe, Structure Technologies, Zona ASI Incoronata – 81100 Foggia - Italia Abstract In this work the mechanical behaviour of CFRP laminates having an artificial wrinkle introduced in the critical section has been studied in t e Open Hol Tension a d Op n Hole Compression configuration. The experimental test allowed determining the failur mechanism and the knockdown of th ultimate strength n five different configurations. © 2017 The Autho s. Publ shed by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of AIAS 2017 International Conference on Stress Analysis. Keywords: Composite material; CFRP; Wrinkles; Mechanical behaviour 1. Introduction In the last y ars the diffu ion of composite laminates for structural applications is continuously growing nd th experience ighlighted adva tag s and critical point of this kin of aterial. An aware use of t ese aterials requires a critical evaluation of the ffects that the presence of imperfections or defects introduced during manufacturing could provoke on the mechanical behavior and structural performance. Several geometrical irregularities are originated by the difficulty that an operator encounter during placement of fiber or laminate during manufacturing, as reported in Cantwell and Morton (1992). They consist in lack of planarit of plies, introduction of u dulations, partial superposition or wrinkles. In all cases, the real orientation of fibers may differ highly from the one defined in design phase, leading to unexpected stress concentration. I particular, a recurrent and diffu ed imperfection is repres nt d by wrinkles. A large number of mechanisms are involved in 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 0832 297771; fax: +39 0832 297768. E-mail address: riccardo.nobile@unisalento.it * Correspon ing author. Tel.: +39 0832 297771; fax: +39 0832 297768. E-mail address: riccardo.nobile@unisalento.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.2017.12.044