PSI - Issue 8

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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. AIAS 2017 International Conference on Stress Analysis, AIAS 2017, 6–9 September 2017, Pisa, Italy Structural analysis of transversally loaded quasi-isotropic rectilinear orthotropic composite circular plates with Galerkin method V.G. Belardi a , P. Fanelli b , F. 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 Bending analysis of rectilinear orthotropic composite plates have bee scarcely investigated taking int a count the increasing use of composite materials in structural applications in the last years. This kind of plates are laminates with axisymmetric geometry and they are made up of unidirectionally reinforced layers with di ff erent orientations. Transversally loading this kind of circular plates, the deflected mid-surface is not independent from the circumferential coordinate, unlike the case of isotropic circular plate. Nevertheless, the quasi-isotropic stacking sequence makes still possible to introduce the hypothesis of axisymmetry for the mid-surface deflection under transversal load, disregarding the circumferential variation of the vertical displacement connected to the variable bending sti ff ness. Then, the constitutive equations for this specific family of plates were obtained finding the stress resultants-strains relations in the global cylindrical coordinate system. These expressions, along with the equilibrium equations, made it possible to derive the governing equation of the problem in the frame of Kirchho ff -Love hypothesis of the classical lamination theory. The Galerkin method was applied to solve the governing third order di ff erential equation in terms of mid-surface deflection, introducing appropriate polynomial approximation functions compliant with the boundary conditions. In particular, fully clamped constraint conditions were considered for the outer diameter of the plate in conjunction with an internal rigid core. The characteri zation of this mo el allows to defin the sti ff n ss matrix terms of a custom composite bolted joint finite element, that i the object of future developments of this work. R su ts of the original propos d method are presented and compared to those obtained by means of FEA p rform d with a refined reference model, demonstrating a good ag eement. c 2017 The Authors. Published by Elsevier B.V. r-review under responsibility of the Scientific Com ittee of AIAS 2017 International Conference on Stress Analysis. Keywords: rectilinear orthotropic composite material; circular plates; bolted connections; Galerkin method; AIAS 2017 International Conference on Stress Analysis, AIAS 2017, 6–9 September 2017, Pisa, Italy Structural analysis of transversally loaded quasi-isotropic rectilinear orthotropic composite circular plates with Galerkin method V.G. Belardi a , P. Fanelli b , F. Vivio a, ∗ a Department of Enterprise Engineering - Univ rsity 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 Bending analysis of rectilinear orthotropic composite plates have been scarcely investigated taking into account the increasing use of composite mate ials in structural pplications in the last yea s. This kind of plates are laminates with axisymmetric geometry and they are made up of unidirectionally reinforced layers with di ff erent orientations. Transversally loading this kind of circular plates, the deflected mid-surface is not independent from the circumferential coordinate, unlike the case of isotropic circular plate. Nevertheless, the quasi-isotropic stacking sequence makes still possible to introduce the hypothesis of axisymmetry for the mid-surface deflection under transversal load, disregarding the circumferential variation of the vertical displacement connected to the variable bending sti ff ness. Then, the constitutive equations for this specific family of plates were obtained finding the stress resultants-strains relations in the global cylindrical coordinate system. These expressions, along with the equilibrium equations, made it possible to derive the governing equation of the problem in the frame of Kirchho ff -Love hypothesis of the classical lamination theory. The Galerkin method was applied to solve the governing third order di ff erential equation in terms of mid-surface deflection, introducing appropriate polynomial approximation functions compliant with the boundary conditions. In particular, fully clamped constraint conditions were considered for the outer diameter of the plate in conjunction with an internal rigid core. The characteri zation of this model allows to define the sti ff ness matrix terms of a custom composite bolted joint finite element, that is the object of future developments of this work. Results of the original proposed method are presented and compared to those obtained by means of FEA performed with a refined reference model, demonstrating a good agreement. c 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: rectilinear orthotropic composite material; circular plates; bolted connections; Galerkin method; © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. 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 Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation.

∗ Corresponding author. Tel.: + 39 06 72597123. E-mail address: vivio@uniroma2.it ∗ Corresponding author. Tel.: + 39 06 72597123. E-mail address: vivio@uniroma2.it

* 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. 2210-7843 c 2017 The Authors. Published by Elsevier B.V. Peer-revi w under responsibility of the Scientific Committee of AIAS 2017 International Conference on Stress Analysis. 2210-7843 c 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 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.2017.12.037