PSI - Issue 4

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com cienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 P o edi Structural Integr ty 4 (2017) 35–41 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2017) 000 – 000 il l li t . i i t. tr t ral Int 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. ESIS TC24 Workshop "Integrity of Railway Structures", 24-25 October 2016, Leoben, Austria Dynamic aspects during full scale rotating bending axle tests using new generation of facilities with increased load frequency Ivo Černý a, * a SVÚM a.s., Tovární 2053, 25088 Čelákovice, Czech Republic According to EN 13261, EN 13103, EN 13104, rotating bending fatigue tests of full scale axles are one of the requested tests, when a new axle type, new material supplier or new manufacturer is intending to provide components for railway rolling stock. One of the test methods, how to generate the rotating bending moment, is to attach the half wheelset using the wheel to the horizontal ground base and to rotate an eccentric mass on the axle top. Such principle is used in the majority of test rigs available on the market. In the past, typical load frequency was 15 – 17 Hz. Under such conditions, only dynamic forces of the eccentric mass could be considered. However, recent design changes of the Sincotec facilities have resulted in increase of test frequencies to more than 25 – 30 Hz, which m kes the tests significantly shorter. On the ther h nd, unlik the previ us case, dy amic aspects of loading calibration have to be considered. A detailed example is shown and discussed. At static loading, the experimentally evaluated stresses on the axle surface corresponded to theoretical values exactly with the exception of near hub edge area, where an expected stress redistribution occurred. When the axle was loaded dynamically by rotating bending, the stress distribution on the axle surface was changed due to additional centrifugal forces of the axle itself, whereas at test frequencies around 30 Hz, such additional forces could no more be neglected. Note that the new character of load distribution cannot be always considered as optimum. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ESIS TC24. , a . ., í , l i , li i t , , , t ti i ti t t ll l l t t t t , l t , t i l li t i i t i t i t il lli t . t t t t , t t t t ti i t, i t tt t l l t i t l t t i t l t t t t i t l t . i i l i i t j it t t i il l t t. t t, t i l l . iti , l i t t i l i . , t i t i t iliti lt i i t t i t t , i t t t i i i tl t . t t , li t i , i t l i li ti t i . t il l i i . t t ti l i , t i t ll l t t t l t t ti l l tl it t ti , t t i t i ti . t l l i ll t ti i , t t i t i ti t l t iti l t i l t l it l , t t t i , iti l l l t . t t t t t l i t i ti t l i ti . t ors. P li l i . . Peer- i i ilit t i ti i itt . Copyright © 2017. Th Auth rs. Published by Elsevier B.V. Peer-review und r responsibility f the Sci nt fic Committe of ESIS TC24. Abstract

© 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Keywords: Full scale fatigue tests; rotating bending; railway axle; dynamic effects : Full scale f ti t t ; r t ting bending; r il ay axle; i ff t

Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation.

* Corresponding author. Tel.: +420-326509050. E-mail address: Ivo.Cerny@seznam.cz i t r. l.: - . - il : I . 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 Copyright  2017. The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ESIS TC24 10.1016/j.prostr.2017.07.003 * Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt 2452-3216 © 2017 The Authors. Published by Elsevier B.V. Peer-review und r responsibil ty of the Scientific Committee of ESIS TC24. t r . li l i r . . i i il t t i ti i itt . -