PSI - Issue 7

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com ScienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 7 (2017) 497–504 Structural Integrity Procedia 00 (2017) 000–000 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2017) 000–000 ScienceDirect

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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. Pub ished by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of the 3rd International Symposium on Fatigue Design and Material Defects. 3rd International Symposium on Fatigue Design and Material Defects, FDMD 2017, 19-22 September 2017, Lecco, Italy Effect of elevated temperature on the fatigue strength of casted AlSi8Cu3 aluminium alloys C. Garb*, M. Leitner, F. Grün Montanuniversität Leoben, Chair of Mechanical Engineering, Franz-Josef-Strasse 18, 8700 Leoben, Austria Abstract In this paper, the fatigue strength of casted aluminium alloy AlSi8Cu3 T5 and T6 is investigated at room and an elevated temperature of 150 °C. The specimens are extracted from cylinder heads (AlSi8Cu3 T5) at one and from crankcases (AlSi8Cu3 T6) at two defined specimen locati ns. In addition, quasi-static tensile tests are executed for both temperature co ditions. Extensive fractographic analyses of tested specimens are performed to characterise the failure mechanisms and measure the crack initiating defect size. This work is supported by computed tomography analysis to achieve an enhanced knowledge of the micropore morphology. The experiments demonstrate that the fatigue strength of the AlSi8Cu3 T5 (cylinder head) and the position 1 of the AlSi8Cu3 T6 (crankcase) significantly decreases at 150 °C by 25 % and 7 % respectively. These two specimen positions exhibit smaller micropore sizes (120 µm and 85 µm at room temperature) compared to position 2 of AlSi8Cu3 T6 (crankcase) and show a partially change in the failure mechanism from defect at room temperatur to li band i uced crack initiation at 150 °C. Position 2 of AlSi8Cu3 T6 ( ankcase) indicates a partial change of the fatigue strength level at 150 °C compared to room tem erature. Additionally it illustrates no change in failure mechanism, whereby all specimens rev al defect induced failure, which can be explained by significant higher micropore sizes (537 µm at room temperature) compared to the other extraction positions. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of the 3rd International Symposium on Fatigue Design and Material Defects. Keywords: micropores; elevated temperature; slip bands; failure mechanism 3rd International Symposium on Fatigue Design and Material Defects, FDMD 2017, 19-22 September 2017, Lecco, Italy Effect of elevated temperature on the fatigue strength of casted AlSi8Cu3 aluminium alloys C. Garb*, M. Leitner, F. Grün Montanuniversität Leoben, Chair of Mechanical Engineering, Franz-Josef-Strasse 18, 8700 Leoben, Austria Abstract In this paper, the fatigue strength of casted alu i ium alloy AlSi8Cu3 T5 and T6 is investigated at room and an elevated tempera ure 150 °C. The specimens are ext acted fr m cylin er h ad (AlSi8Cu3 T5) at one and from crankcases (AlSi8Cu3 T6) at two defined specimen locations. In addition, quasi-static tensile tests are executed for both temperature conditions. Extensive fractographic analyses of tested specimens are performed to characterise t e failure mechanisms and measure the crack initiating defect size. This work is supported by computed tomograph analysis to achieve an enhanced knowledge of the micropore morphology. The experiments demonstrate that the fatigue strength of the AlSi8Cu3 T5 (cylinder head) and the position 1 of the AlSi8Cu3 T6 (crankcase) significantl decreases at 150 °C by 25 % and 7 % respectively. These two specimen positions exhibit smaller micropore sizes (120 µm and 85 µm at room temperature) compared to position 2 of AlSi8Cu3 T6 (crankcase) and show a partially change in the f ilure mechanism from defect t room temperature to sl p band induced crack initiation at 150 °C. Position 2 of AlSi8Cu3 T6 (crankcase) indicates a partial chang of th fa igue strength level at 150 °C compared to room temperature. Additionally it illustr t s no change in failure mechanism, whereby all speci ens reveal a d fect induced failure, which can be explained by significant higher micropore sizes (537 µm at room temperature) compared to the other extraction positions. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of the 3rd International Symposium on Fatigue Design and Material Defects. Keywords: micropores; elevated temperature; slip bands; failure mechanism © 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.: +43 3842 402-1411; fax: +433842402-1402. E-mail address: christian.garb@unileoben.ac.at

2452-3216 © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of the 3rd International Symposium on Fatigue Design and Material Defects. 2452-3216 © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of the 3rd International Symposium on Fatigue Design and Material Defects. * Corresponding author. Tel.: +43 3842 402-1411; fax: +433842402-1402. E-mail address: c ristian.garb@unileoben.ac.at

* Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt

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 the 3rd International Symposium on Fatigue Design and Material Defects. 10.1016/j.prostr.2017.11.118