PSI - Issue 5
ScienceDirect Available online at www.sciencedirect.com Available o line at ww.sciencedirect.com ienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 5 (2017) 115–122 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. 2nd International Conference on Structural Integrity, ICSI 2017, 4-7 September 2017, Funchal, Madeira, Portugal Hygrothermomechanical Behavior of Thick Composite Plates Using High Order Theory B.Boukert a, *, A.Benkhedda a ,E.A.Adda Bedia b M.Khodjet-Kesba a a Laboratoire des Sciences Aéronautiques, Institut d’Aéronautique et des études spatiales, Université de Blida 1, B.P 270 route de Soumaa,Algérie b Laboratoire de Matériaux et Hydrologie, Université de Sidi Bel Abbès,Algérie Abstract The structures made of composite materials represent a very great part of research in aeronautical and aerospace engineering considering their specific characteristics in term of lightness and rigidity. During service these structures are subjected to changely environmental conditions that sometimes are extremely in term of temperature and humidity which cause residual stresses. The determination of this stress is highly significant for the reliability of the design stages and dimensioning. This study investigates the behaviour of thick composite laminates using the high order method through stresses calculation. T e c mposite plate is subjecte to mechanical solicitation and working in a hygrothermal environment. Temperature and humidity re taken into account in the calculation o stresses. D ifferent simula i ns r carried out for different profile of temperature and concentration distribution (linear, constant, parabolic, etc.) to observe the response of structures. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. 2nd International Conference on Structural Integrity, ICSI 2017, 4-7 September 2017, Funchal, Madeira, Portugal Hygrothermomechanical Behavior of Thick Composite Plates Using High Order Theory B.Boukert a, *, A.Benkhedda a ,E.A.Adda Bedia b M.Khodjet-Kesba a a Laboratoire des Sciences Aéronautiques, Institut d’Aérona tique et des études spatiales, Université de Blida 1, B.P 270 route de Soumaa,Algér e b Laboratoire de Matériaux et Hydrologie, Université de Sidi Bel Abbès,Algérie Abstract The structures made of composite materials represent a very reat part of research in aeronautical and aerospace engineering considering their specific characteristics in ter of lightness and rigidity. During service these structures are subjected to changely environmental conditi s that sometimes are extremely in term of temperature and humidity which cause residual stresses. The determination of this stress is highly significant for the reliability of the design stages and dimensioning. This study investigates the behaviour of thick composite laminates using the hi h order met od through stresses calculation. Th comp site plate is subjected to mechani l solicitation a d working in a hygrothermal environment. Temp ratu e and humidity are taken i to account in the calcul tion of stresses. D ifferent simulations are car ied out for diff rent profile of temperature and concentration distribution (lin ar, constant, parabolic, etc.) to observe the response of structures. © 2017 The Authors. Publ shed by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. © 2017 The Author . P blished by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017
© 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Keywords: Thick Plates, Hygrothermal , High Order; Keywords: Thick Plates, Hygrothermal , High Order;
Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation.
* Corresponding author. E-mail address: bilanosky@hotmail.fr * Correspon ing author. E-mail address: bilanosky@hotmail.fr
2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. 2452-3216 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017 10.1016/j.prostr.2017.07.076 * Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt 2452 3216 © 2017 Th Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. 2452-3216 © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017.
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