PSI - Issue 6

ScienceDirect Available online at www.sciencedirect.com Available o line at www.sciencedire t.com ScienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 6 (2017) 14 –145 Available online at www.sciencedirect.com ScienceDirect StructuralIntegrity Procedia 00 (2017) 000–000 Available online at www.sciencedirect.com ScienceDirect StructuralIntegrity 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 © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the MCM 2017 organizers. XXVII International Conference “Mathematical and Computer Simulations in Mechanics of Solids and Structures”. Fundamentals of Static and Dynamic Fracture (MCM 2017) Generalized Flexibility Method by the Example of Plane Elastoplastic Problem Meleshko V.A., Rutman Y.L.* Saint-Petersburg State University of Architecture and Civil Engineering, 2-ya Krasnoarmeiskaya st., 4 Saint-Petersburg , 190005, Russia Abstract The structures elastoplastic deformation process can be studied using the finite elements method (FEM). However, to perform reliable, adequate and real calculations of structures, it is necessary to create large finite element models and to use large-scale software systems for their analysis. Thousands or tens of thousands of equations are involved in it. These calculations take much time. Application of the flexibility method developed on the bases of generalized Mohr formula (generalized flexibility method) allows to create numerical algorithms for elastoplastic calculation of framed structures and to obtain adequate results with no significant processor and time consumption. As a result, a number of preparatory operations increases, however, a number of algebraic equations at each step equals to the number of framed structures indetermination only. © 2017 The Authors. Publishe by Elsevier B.V. Pe r-review under respon ibility of the MCM 2017 organizers. Keywords: generalized flexibility method; integral function of state law of secti n; tangent stiffness; elastoplastic eform tion * Corresponding au hor. Tel.: +7-921-748-07-16. E-mail address: vl-meleshko@yandex.ru 1. Introduction Today software systems based on the finite elements method (FEM) are used for engineering calculations. When nonlinear problems related to elastoplastic processes in structures are solved by this method, time consumed by processor highly increases that is frequently unacceptable under the design conditions. In many cases, to calculate construction structures, the framed structures are used, which cover the large range of engineering problems. For these systems, elastoplastic problems can be solved with generalization of conventional methods of structural mechanics. This generalization intends using explicit time computational scheme and determining the system’s tangential stiffness at each step. The approach based on the generalized flexibility method (generalized displacement method) allows to highly reducing a time for elastoplastic problems solution. XXVII International Conference “Mathematical and Computer Simulations in echanics of Solids and Structures”. Fundamentals of Static and Dynamic Fracture (MCM 2017) Generaliz d Flexibility Method by the Example of Plane Elastoplastic Problem Meleshko V.A., Rutman Y.L.* Saint-Petersburg State University of Architecture and Civil Engineering, 2-ya Krasnoarmeiskaya st., 4 Saint-Petersburg , 190005, Russia Abstract The structures elastoplastic deformation process can be studied using the finite el ments m thod (FEM). However, to p rform reliable, adequate and r al c lculations of structur s, it is necessary to cre te large f nite elemen models and to use l rg -scale software systems f r t ir analysis. Thousands or t ns f ousands of equations are involved in it. These calculat ons take much time. Application of the flexibility eth d developed on the b ses of generalized Mohr formula (gener lized fl xibility me od) allows to create numerical algorithms for elastoplastic calculation of framed structur s and to obtain adequate esults with no si nificant proces or and tim consumption. As a esult, a number of preparatory operations increases, however, a number of algebraic equations at each step equals to the number of framed structures indetermination only. © 2017 The Aut o s. Publ shed by Elsevier B.V. Peer-review under responsibility of the MCM 2017 organizers. Keywords: generalized flexibility method; integr l function of state law of section; tang nt s if ness; elastoplastic defo mation * Corresponding author. Tel.: +7-921-748-07-16. E-mail address: vl-meleshko@yandex.ru 1. Introduction Today software systems based on the finite elements method (FEM) ar used for engineering calculations. When nonlinear problems r lat d to elastoplastic process s in str ctures are solved by this method, time consumed by processor highly increases that is frequently unacceptable under the design conditions. In many cases, to calculat construction structures, the fra ed structures are used, which cover the large range of engineering problems. For these systems, lastoplastic problems can be solved with generaliz tion of conventional methods of structural echanics. This generalization intends using explicit time computational sch me and determining the syst ’s tangential stiffness at each step. The approach b sed on the generalized flexibility method (generalized displacement method) allows to highly reducing a time for elastoplastic problems solution. © 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 2452 3216© 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the MCM 2017 organizers. 2452-3216© 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the MCM 2017 organizers.

2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016.

2452-3216 Copyright  2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the MCM 2017 organizers. 10.1016/j.prostr.2017.11.022