PSI - Issue 12

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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.2018.11.087 ∗ Corresponding author. Tel.: + 39 06 72597123. E-mail address: vivio@uniroma2.it 2210-7843 c 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. ∗ Corresponding author. Tel.: + 39 06 72597123. E-mail address: vivio@uniroma2.it 2210-7843 c 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 r ponsibility of the Scientific ommitt e of AIAS 2018 International Conference on Stress Analysis. 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 n open access article under the CC BY-NC-ND licens (http://creativecommons.org/licenses/by-nc-nd/3.0/) Peer-review und r responsibility of the Scientific Commi tee of AIAS 2018 International Conferen e on St ess Analysis. AIAS 2018 International Conference on Stress Analysis A novel composite bolted joint element: application to a single-bolted joint Valerio G. Belardi a , Pierluigi Fanelli b , Francesco Vivio a, ∗ a Department of Enterprise Engineering - University of Rome Tor Vergata, Via del Politecnico, 1, 00133, Rome, Italy b Department of Economics, Engineering, Society and Busin ss Organization, University of Tusc a, Largo dell’Universita` , 01100 Viterbo, Italy Abstract Based on an analytical solution of the theoretical reference model of the composite bolted joint undergoing in-plane loads, a modeling technique for this kind of demountable connections is presented. The novel composite bolted joint element substitutes a region of the original model, omprising th bolt a d the peripheral area, with a et of radially arranged beams: the cross-section properties are opportunely tailored in order to establish a sti ff ness equivalence between the theoretical reference model and the presented finite element through the resolution of a system of algebraic equations. The in-plane load condition is considered in this work because of its prevalence in comparison with other ones in many practical applications as the double lap shear joint. Numerical case studies are provided to validate the novel composite bolted joint element comparing FE models of circular plates, featuring a quasi-isotropic lay-up, with an internal rigid core or with the presented FE tool. c 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: rectilinear orthotropic composite material; circular plates; bolte co nections Demountable joint c nnections represent a strategic connection method in the overall engineering fields. Moreover, the aeronautic and the aerospace fields are particularly sensible to the proper design of these structural elements and in the evaluation of their influence on the adjacent jointed components stress field, as testified by the published works related to the subject: in McCarthy et al. (2005); McCarthy and McCarthy (2005) a three-dimensional FE model is developed; the work by Gray and Mccarthy (2011) depicts the definition of a user-defined finite element to describe the load distribution of bolted composite structures; Kapidzˇic´ et al. (2014); Chowdhury et al. (2016) provided specific insights for aircraft structures applications. Specifically, the necessities of developing e ffi cient design tools for composite bolted joints is particularly relevant in aerospace design. As an example, considering anisogrid composite lattice structures that are progressively replacing AIAS 2018 International Conference on Stress Analysis novel co posite bolted joint ele ent: application to a single-bolted joint Valerio G. Belardi a , Pierluigi Fanelli b , Francesco Vivio a, ∗ a Department of Enterprise Engineering - University of Rome Tor Vergata, Via del Politecnico, 1, 00133, Rome, Italy b Department of Economics, Engineering, Society and Business Organization, University of Tuscia, Largo dell’Universita` , 01100 Viterbo, Italy Abstract Based on an analytical solution of the theoretical reference model of the composite bolted joint undergoing in-plane loads, a modeling technique for this kind of demountable connections is presented. Th novel composite bolted joint element substitutes a region of the original model, comprising the bolt and the peripheral area, with a set of radially arranged beams: the cross-section properties are opportunely tailored in order to establish a sti ff ness equivalence between the theoretical reference model and the presented finite element through the resolution of a system of algebraic equations. The in-plane load condition is considered in this work because of its prevalence in comparison with other ones in many practical applications as the double lap shear joint. Numerical case studies are provided to validate the novel composite bolted joint element comparing FE models of circular plates, featuring a quasi-isotropic lay-up, with an internal rigid core or with the presented FE tool. c 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- c-nd / 3.0 / ) er-review unde responsibility of th Scientific Committee of AIAS 2018 International Conference on Stress Analysis. Keywords: rectilinear orthotropic composite material; circular plates; bolted connections 1. Introduction Demountable joint connections represent a strategic connection method in the overall engineering fields. Moreover, the aeronautic and the aerospace fields are particularly sensible to the proper design of these structural elements and in the evaluation of their influence on the adjacent jointed components stress field, as testified by the published works related to the subject: in McCarthy et al. (2005); McCarthy and McCarthy (2005) a three-dimensional FE model is developed; the work by Gray and Mccarthy (2011) depicts the definition of a user-defined finite element to describe the load distribution of bolted composite structures; Kapidzˇic´ et al. (2014); Chowdhury et al. (2016) provided specific insights for aircraft structures applications. Specifically, the necessities of developing e ffi cient design tools for composite bolted joints is particularly relevant in aerospace design. As an example, considering anisogrid composite lattice structures that are progressively replacing © 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.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt 1. Introduction