PSI - Issue 13

ScienceDirect Available online at www.sciencedirect.com Available online at ww.sciencedire t.com ienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structural Integrity 13 (2018) 16 9–1614 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2018) 000–000 Available online at www.sciencedirect.com ScienceDirect Structural I t gri y 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. © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. ECF22 - Loading and Environmental effects on Structural Integrity Surface machining condition and fatigue life on Inconel 718 A. Martin-Meizoso* a , J.M. Martinez-Esnaola a , P.J. Arrazola b , A. Linaza c a Tecnun Ceit-IK4 (University of Navarra), P. Manuel Lardizabal 15, San Sebastian 20018, Spain b Faculty of Engineering, Mondragon University, Loramendi 4, Arrasate 20500, Spain c ITP Aero, Parque Tecnológico, Edifico 300, Zamudio 48170, Spain Abstract Life assessment of components working in aero-engines at elevated temperatures is critical. Machining has a serious effect on these nickel-based alloys, for example in turbine discs, affecting their life in service. Machining (turning, broaching…) modifies surface roughness, thickness of the affected substrate layer (including the effect of possible broken carbides) and residual stress distribution near the component surface. On top of that, it is possible to sh t-peen or not the component, which again modifies its surface integrity. The aim of this work is to discern among the effect of the different parameter: roughness, damage and residual stresses on fatigue performance and optimum machining conditions. © 2018 The Authors. Published by Elsevier B.V. Peer-review under resp sibility of the ECF22 organizers. Keywords: Machining; Surface Condition; Fatigue; High Temperature; Inconel 718 1. Introduction Life assessment of c mpon nt that work at high temperatures is essential for their proper performance and simple maint nance, especially for critical components whose failure eed t be avoided. For their assessment, fatigue tests are carried out on test-pieces of reference material. Surface condition, a consequence of machining procedures on component manufacture, plays a key role on their future in-service behavior, and –more relevant- in fatigue life. Within the framework of a European project (ENOVAL), one part of the research is devoted to the study of fatigue behavior of representative specimens on Inconel 718, having turned surfaces generated of Inconel 718, under different machining conditions: cutting speeds, tool advance, tool edge wear… what introduce different depths for the ECF22 - Loading and Environmental effects on Structural Integrity Surface machining condition and fatigue life on Inconel 718 A. Martin-Meizoso* a , J.M. Martinez-Esnaola a , P.J. Arrazola b , A. Linaza c a Tecnun Ceit-IK4 (University of Navarra), P. Manuel Lardizabal 15, San Sebastian 20018, Spain b Facul y of Engineering, Mondragon University, Loramendi 4, Arrasate 20500, Spain c ITP Aero, Parque Tecnológico, Edif co 300, Zamudio 48170, Spain Abstract Life assessment of components working in aero-engines at elevated temperatures is critical. Machining has a serious effect on these nickel-based alloys, for example in turbine discs, affecting their life in service. Machining (turning, broaching…) modifies surfac roughness, thickness of the affected su strate layer (including the effect of possible broken carbides) and residual stress distribution near th component surface. On top of that, it is possible to shot-peen or ot the component, which again modifies its surface integrity. The aim of this work is to discern among the effect of the different parameter: roughness, damage and residual stresses on fatigue perfor ance and optimum machining conditions. © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. Keywords: Machining; Surface Condition; Fatigue; High Temperature; Inconel 718 1. Introduction Life assessment of compon nts that work at igh temperatures is essential for their proper perf rmance and simple maintenance, especially for critical components whose failure need to be avoided. For their ass ss ent, fatigue tests are carried out on test-pieces of reference material. Surface condition, a consequence of machining procedures on component manufacture, plays a key role on their future in-service behavior, and –more relevant- in fatigue life. Within the framework of a European project (ENOVAL), one part of the research is devoted to the study of fatigue behavior of representative specimens on Inconel 718, having turned surfaces generated of Inconel 718, under different machining conditions: cutting speeds, tool advance, tool edge wear… what introduce different depths for the © 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.: +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 organizers. * Corresponding author. Tel.: +34 943212800; fax: +34 943213076. E-mail address: ameizoso@ceit.es * Corresponding author. Tel.: +34 943212800; fax: +34 943213076. E-mail ad ress: ameizoso@ceit.es

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.2018.12.339