PSI - Issue 7

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com Sci ceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 7 (2017) 124–132 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. 3rd International Symposium on Fatigue Design and Material Defects, FDMD 2017, 19-22 September 2017, Lecco, Italy Evaluation on Tensile and Fatigue Crack Growth Performances of Ti6Al4V All y Produced by Selective Laser Melting Z.H. Jiao a , R.D. Xu a , H.C. Yu a * , X.R. Wu a a Aviation Key Laboratory of Science and Technology on Materials Testing and Evaluation, Science and Technology on Advanced High Temperature Structrual Materials Laboratory, Beijing Key Laborotory of Aeronautical Materials Testing and Evaluation, Beijing Institute of Aeronautical Materials, Beijing 100095, China Additive manufacturing (AM) technologies are increasing in importance for aerospace application, where the demand for a fundamental unde standing and predictability of sta c and dynamic material properties are high. As the most widely used and studied alloy for this technology, Selective laser melting (SLM) produced Ti6Al4V alloy is evaluated on tensile and fatigue crack growth (FCG) performances at RT and 400 ℃ . Conventionally manufactured Ti6Al4V alloys are concerned for comparison. Different orientations are considered to investigate the anisotropy of tensile and FCG behavior. The results show that, the tensile properties at RT and 400 ℃ are highly dependent on the specimen orientation relative to build direction. The FCG resistance is related to sp cimen orie tation in the ne r threshold regi n but no relationship with specimen orientatio in the steady growth stage at RT. The FCG istance is much less influenced by spec men orien ation at 400 ℃ . The tensil strength at RT an 400 ℃ of SLM alloy reaches even exceeds the strength level of co ventionally anufactured alloys such as forging, bar and casting. The steady stage FCG resistance under stress ratio of 0.1 of SLM alloy is also comparable to conventionally manufactured alloys. The SLM alloy shows higher FCG resistance under stress ratio of 0.1 than 0.5, but the d a /d N - △ K curves of the two stress ratios are very close to each other. The steady stage FCG rate at RT is slower than 400 ℃ in the lower △ K region and faster in the higher △ K region. © 2017 The Authors. Published by Els v er 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 Evaluation on T sile and Fatigue Crack Growth Performan es of Ti6Al4V Alloy Produced by Selective Laser Melting Z.H. Jiao a , R.D. Xu a , H.C. Yu a * , X.R. Wu a a Aviation Key Laboratory of Science and Techn logy on Materials Test ng and Evaluatio , Science and Technology on Advanced High Temperature Structrual Materials Laboratory, Beijing Key Laborotory of Aeronautical Materials Testing and Evaluation, Beijing Institute of Aeronautical Materials, Beijing 100095, China Abstract Additive manufacturing (AM) technologies are increasing in importance for aerospace application, where the demand for a fundamental understanding and predictability of static and dynamic material properties are high. As the most widely used and studied alloy for this technology, Selective laser melting (SLM) produced Ti6Al4V alloy is evaluated on tensile and fatigue crack growth (FCG) performances at RT and 400 ℃ . Conventionally manufactured Ti6Al4V alloys are concerned for comparison. Different orientations are considered to investigate the anisotropy of tensile and FCG behavior. The results show that, the tensile properties at RT and 400 ℃ are highly dependent on the specimen orientation relative to build direction. The FCG resistance is related to specimen orientation in the near threshold region but no relationship with specimen orientation in the steady growth stag at RT. The FCG resistance is much less influenced by pecimen orientation at 400 ℃ . The tensile strength at RT and 400 ℃ of SLM alloy r aches even exceeds the strength level of conventionally manufactured alloys such as f rging, bar and casting. The steady stage FCG resistance under stress ratio of 0.1 of SLM alloy is also comparable to conventionally manufactured alloys. The SLM alloy shows higher FCG resistance under stress ratio of 0.1 than 0.5, but the d a /d N - △ K curves of the two stress ratios are very close to each other. The steady stage FCG rate at RT is slower than 400 ℃ in the lower △ K region and faster in the higher △ K region. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Com ittee of the 3rd International Symposium on Fatigue Design and Material D fects. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. 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. Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation. Keywords: SLM; tensile properties; fatigur crack growth; anisotropy; elevated temperature. Keywords: SLM; tensile properties; fatigur crack growth; anisotropy; elevated temperature. Abstract

* Corresponding author. Tel.: +86-10-62496718; fax: +86-10-62496733. E-mail address : yhcyu@126.com * Corresponding author. Tel.: +86-10-62496718; fax: +86-10-62496733. E-mail address : yhcyu@126.com

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.: +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.2017.11.069