PSI - Issue 13

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at www.sciencedire t.com ScienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 13 (2018) 59 –595 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2018) 000 – 000 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2018) 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. ECF22 - Loading and Environmental effects on Structural Integrity Characterization of the Long Crack Propagation Behaviour in a Hardenable Aluminium Alloy in Very High Cycle Fatigue Regime F. Bülbül a *, H.-J. Christ a , M. Wicke b , A. Brückner-Foit b , T. Kirsten c , M. Zimmermann c a Institut für Werkstofftechnik, Universität Siegen, D-57068 Siegen, Germany b Institut für Werkstofftechnik, Universität Kassel, D-34125 Kassel, Germany c Institut für Werkstoffwissenschaft, Technische Universität Dresden, D-01069 Dresden, Germany In the regime of Very High Cycle Fatigue (VHCF), it appears questionable whether all the well-known stages of fatigue crack propagation occur. Deviations must be expected through the very small dimension of the cyclic plastic zone ahead of the crack tip and, hence, a strong interaction with microstructural features seems very likely . Investigations have shown that “natural” crack initiation often takes place underneath the material surface leading to crack propagation without contact to atmospheric components. In order to reproduce the crack growth behaviour, an ultrasonic fatigue testing system (USFT) equipped with a small vacuum chamber was used for fatigue experiments in vacuum. The tests were carried out on the alum ium alloy EN-AW 6082 in the peak ag d (pa) condition. Micro-notches w re prepared in the USFT specimens by means of the Focused-Ion-B am technique. Syst matic measurements in laboratory a r in the region of the threshold valu of long fatigue crack growth rev aled that primary pr cipitates signifi antly influence the crack growth behaviour. Depending on the spatial distribution of the primary precipitates, strong crack retardatio and localized crack arrest take place even far bove the threshold value. In vacuum only shear-stress-controlled VHCF long crack propagation were detected in EN-AW 6082 (pa) due to very pronounced single dislocation slip associated with the secondary precipitates of the aluminium alloy. © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. © 2018 Th Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. ECF22 - Loading and Environmental effects on Structural Integrity Characterization of the Long Crack Propagation Behaviour in a Hardenabl Aluminium Alloy in Very High Cycle Fatigu Regime F. Bülbül a *, H.-J. Christ a , M. Wicke b , A. Brückner-Foit b , T. Kirsten c , M. Zimmermann c a Institut für Werkstofftechnik, Universität Siegen, D-57068 Siegen, Germany b Kassel 34125 Kassel c Institut für Werkstoffwissen chaft, Technisch Universität Dresden, D-01069 D esden, Germany Abstract In the regime of Very High Cycle Fatigue (VHCF), it appears questionable whether all the well-known stages of fatigue crack propagation occur. Deviations must be exp cted through the very small dimension of the cyclic p astic zo e h ad of the cra k tip and, hence, a strong interaction with microstructu al features see s very likely . Investigations have shown th t “natural” rack i itiatio often takes place underneat the material surface leading to crack propagation without contact to atmospheric components. I orde to reproduce th crack growt behav our, an ultr so ic fatigue testin system (USFT) equipped wit a small vacuum chamb was use for fatigue expe iments in vacuum. The te ts were carried out on the aluminium alloy EN-AW 6082 in the peak aged (pa) conditi n. M cro-notch s were prepared in the USFT specimens y m ans of the Focused-Ion-Beam technique. Systematic m asurements in laboratory air in the gion of th thr s old value of long fatigue c ack gr wth reveal d that rimary precipit tes significantly influence the crack growth behaviour. Depending on the spatial distribution of the primary preci itates, strong crack retardation and localized crack arrest take pl ce even far above the threshold value. In vacuum only shear-stress-controlled VHCF long crack propag tion were detected in EN-AW 6082 (pa) due to very pronounced single dislocation slip ass ciated with the secondary precipitates of the aluminium alloy. © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. Keywords: Hardenable aluminium alloy; Very High Cycle Fatigue; shear-stress-controlled VHCF long crack propagation; barrier effect © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Keywords: Hardenable aluminium alloy; Very High Cycle Fatigue; shear-stress-controlled VHCF long crack propagation; barrier effect Abstract

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

* Corresponding author. Tel.: +49 271-740-4627 E-mail address: fatih.buelbuel@uni-siegen.de * Corresponding author. Tel.: +49 271-740-4627 E-mail ad ress: fatih.bu buel@uni-siegen.de

* Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt 2452-3216 © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. 2452-3216 © 2018 The Authors. Published by Elsevier B.V. Peer review under r sponsibility of the ECF22 o ganizers.

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

2452-3216  2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. 10.1016/j.prostr.2018.12.097