PSI - Issue 5

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com cienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 5 (2017) 861–868 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 ( )

www.elsevier.com/locate/procedia . l i r. /l t / 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 Investigations on crack propagation in wheelset axles under rotating bending and mixed mode loading Robert Hanneman a *, Paul Köster a , Manuela Sander a a Institute of Structural Mechanics (StM), University of Rostock, Albert-Einstein-Str. 2, 18055 Rostock, Germany Failures in wheelset axles can lead to catastrophic consequences. In order to prevent unexpected failures, inspection intervals must be defined based on fracture mechanical app oache . For the railway axle steel 34CrNiMo6 fatigue crack growth data have been experimentally determined for a range of different negative stress ratios and the FORMAN / METTU parameters for different probabilities of survival are identified. For the investigation of the influence of the transition radii on the crack growth behavior, different shouldered solid shafts are designed and tested under rotating bending load. Moreover, at special wheel rail situations the bending load is overlapped with torsional loading. Hence, to examine this influence on the fatigue crack growth in wheelset axles a test rig for mixed mode load situations has been developed. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. Keywords: Fatigue crack growth, rotating bending, mixed mode loading, constant amplitude loading, wheelset axles 1. In roduction Wheelset axles are regularly non-destructively inspected in defined intervals in order to prevent unexpected failures and to assure a safe life. In current practice, relevant inspection intervals are often determined on the basis of experiences (Gänser et al. (2016); Mädler, Geburtig and Ullrich (2016)). However, a theoretical well-substantiated specification of the inspection intervals can be made by a reliable computed remaining lifetime prediction using fracture-mechanical approaches. In contrast to the crack propagation models of thin sheet metal structures e.g. from the aerospace industry the models for remaining lifetime calculations of thick-walled shaft structures with non-linear ert a I tit t f t t l i ( t ), i it f t , l t- i t i - t . , t , il i l t l l t t t i . t t t il , i ti i t l t i t i l . t il l t l i ti t t i t ll t i i t ti t ti t / t i t iliti i l i ti i . t i ti ti t i l t t iti ii t t i , i t l li t i t t t ti i l . , t i l l il it ti t i l i l it t i l l i . , t i t i i l t ti t i l t l t t i i l it ti l . t . li l i . . Peer-review under responsibilit t e Scientific itt f ICS 17. Keywords: Fatigue crack growth, rotating bending, mixed mode loading, constant amplitude loading, wheelset axles . t i l t l l l t ti l i t i i i t l i t t t il t li . t ti , l t i ti i t l t t i t i i t l. ; l , ti ll i . , t ti l ll t ti t sp i i ti t i ti i t l li l t i i li ti i ti i t i l . t t t t ti l t i t t l t t . . t i t t l i i li ti l l ti t i ll t t t it li © 2017 The Authors. Published by Elsevier B.V. Peer-review u der r sponsibility 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. Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation. Abstract

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.2017.07.104 * 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 . * Corresponding author. Tel.: +49 (0) 381 498-9341; fax: +49 (0) 381 498-9342. E-mail address: robert.hannemann2@uni-rostock.de i t r. l.: ( ) - ; f : ( ) - . - il : r rt. i-r t . - t r . li rr