PSI - Issue 5

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com ienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 5 (2017) 233–238 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2017) 000 – 000 il l li t . i i t. tr t r l I t rit r i ( )

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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 Stable crack growth in composite laminates under various stiffness of the loading system Tretyakov M.P. a *, Wildemann V.E. a a Center of Experimental Mechanics, Perm National Research Polytechnic University, 29 Komsomolskiy Ave., Perm, 614990, Russia The work is devoted to experiment l study of stable and unstable crack growth processes in composite materials. The eccentric tension tests of the compact specimens of glass-epoxy composite laminates in conditions of various stiffness of the loading system were carried out. Different measurement techniques of crack opening displacement were used in work. During the analysis of results of a tension test of compact specimens with crack, descending sections of the loading curves were considered by analogy with postcritical deformation stage, which could be found in test of smooth specimens of different materials. It is shown that behavior of composite specimens with crack under tension depends on the loading system parameters: crack grows process is stable when stiffness of the loading system is enough, crack opening displacement rate increase under reduction of stiffness of the loading system. This effect should be take into account during modeling and analyzing of fracture processes of composite materials, strength and survivability assessment of composite structures in real loading conditions. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. Keywords: stable crack growth, composite laminates, loading system stiffness, postcritical deformation stage, compact specimen tension tests,. deira, P a a t f i t l i , ti l l t i i it , lski ., , , i i t t i t l t t l t l t i it t i l . t i t i t t t t i l it l i t i iti i ti t l i t i t. i t t t i i i l t i . i t l i lt t i t t t i it , i ti t l i i l it t iti l ti t , i l i t t t i i t t i l . t i t t i it i it t i t l i t t : i t l ti t l i t i , i i l t t i ti ti t l i t . i t l t i t t i li l i t it t i l , t t i ilit t it t t i l l i iti . t . li l i . . Peer-revie i ility of the ientifi itt CSI 2017. Keywords: stable crack growth, composite laminates, loadi t tiff , t ritical def rm tion stage, comp t i tension tests,. © 2017 The Authors. Published 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. The crack growth rocess in composite materials has been the object of a large number of studies over more than two decades. It connected with extensive use of composite materials in different technical fields, especially in aeronautical engineering, and high requirements for structural integrity. From the point of view of safety and t i t t i l t j t l t i t t . t t it t i it t i l i i t t i l i l , i ll i ti l i i , i i t t t l i t it . t i t i t Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation. Abstract 1. Introduction . i

* Corresponding author. Tel.: +7-342-239-1111; fax: +7-342-239-1224. E-mail address: cem_tretyakov@mail.ru i t r. l.: - - - ; f : - - - . - il : tr t il.r rr

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.2017.07.122 * 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 Scientific Committee of ICSI 2017. l i r . . i i ilit t i ti i itt . - t r . li