PSI - Issue 7

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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) 315–32 ScienceDirect Structural Integrity Procedia 00 (2017) 000–000 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2017) 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. Copyright © 2017 The Authors. Published y Els vier B.V. Peer-review under responsibility of he Scientific Com ittee of the 3rd Internation l Symposium on Fatigu Design and M terial D f cts. 3rd International Symposium on Fatigue Design and Material Defects, FDMD 2017, 19-22 September 2017, Lecco, Italy Fatigue limit evaluation of structure materials based on thermographic analysis R. Prochazka*, J. Dzugan, P. Konopik COMTES FHT, Department of mechanical testing and thermophysical measurement, Prumyslova 995, Dobrany 33441, Czech Republic Abstract The work presented here is dealing with implementation of new approach to fatigue limit determination. The approach is based on application of thermography on specimen that is step-by-step increasingly loaded. Detected temperature changes at different stress levels are evaluated and final fatigue limit level is determined.. Thermography analysis seems to have a great potential to reduce the material demand and to achieve the minimum testing time while the quality of test results remains comparable to standard approach. This is extremely useful in cases where the experimental material is strictly limited, such as new materials development, residual service life of in-service components determination or also, nowadays, for additive manufacturing components, where specimens preparation is expensive. Each specimen was tested at different stress amplitudes, where the test procedure consists of at least 8 loading steps. Results obtained with the thermography technique were compared with those obtained from standard high-cycle force-controlled fatigue tests under constant loading until failure in accordance with the ASTM E466-07 standard. All tests were done at room temperature with the cycle asymmetry coefficient R = -1. © 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. 3rd International Symposium on Fatigue Design and Material Defects, FDMD 2017, 19-22 September 2017, Lecco, Italy Fatigue limit evaluation of structure materials base on thermographic analysis R. Prochazka*, J. Dzugan, P. Konopik COMTES FHT, Department of mechanical testing and thermophysical measurement, Prumyslova 995, Dobrany 33441, Czech Republic Abstract Th work pres nted her is deali g with implementation of new approach to fatigue limit determinati n. The approach is b sed on application of thermography on specimen that is step-by-step increasingly loaded. Detected temperature changes at different tress levels are evaluated and final fatigue limit level is d termined.. Thermogr phy analysis seems to have a great potential to reduce the mat rial demand and to achieve the mini um testing time while the quality of test results remains comparable to standard approach. This is extremely useful in cases where the experimental material is strictly limited, such as new materials development, residu l service life of in-service components det rminati n or also, nowadays, for additiv manufacturing components, w re specimens preparation is xpensive. Each specimen w s tested at different str ss amplitudes, where t e test procedure consists of at least 8 loading steps. Results obtained with the thermogr phy techniqu were compared with those obtained from standard high-cycle force-controlled fatigue tests under constant loading until failure in accordance with the ASTM E466-07 standard. All tests were done at room temperatur with the cycle asymmetry coefficient R = -1. © 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 D fects. Keywords: Fatigue limit; thermographic methodology; degradation

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

* Corresponding author. Tel.: +420 377 197 358; fax: +420 377 197 310 E-mail address: radek.prochazka@comtesfht.cz

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.: +420 377 197 358; fax: +420 377 197 310 E-mail address: radek.prochazka@comtesfht.cz

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

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.2017.11.094

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