PSI - Issue 14

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 P o edi Structural Integr ty 14 ( 9) 3–10 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

www.elsevier.com/locate/procedia www.elsevier.com/locate/procedia

www.elsevier.com/locate/procedia

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. © 2019 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0/) Selection and peer-review under responsibility of Peer-review under responsibility of the SICE 2018 organizers. 2nd International Conference on Structural Integrity and Exhibition 2018 Low cycle fatigue of alloys in hot section components: progress in life assessment Luc Rémy* Centre des Matériaux, MINES ParisTech, PSL* Research University, CNRS UMR 7633, BP87, 91003 Evry Cedex, France Abstract Hot section co ponents are exposed to hi h temperature operation a d thermal tran ients during service life. The research of improved performances leads to consider the risk of crack initiation due to isothermal (LCF) or thermal-mechanical (TMF) low cycle fatigue loading in component design. This article gives a short survey of progress in LCF and TMF life estimation procedures due to the description of metallic alloys behavior (superalloys, cast iron, stainless steels). Assessing the lifetime under cyclic loading conditions requires constitutive models accounting for viscoplasticity at service temperatures or during transients. These models can be validated at the laboratory scale using thermal mechanical fatigue tests. Crack initiation life prediction models can be quite simple or need to account for creep-fatigue interactions or environmental effects. Examples illustrate advances in materials studies and models over the years in aero-engine and automotive applications. © 2018 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0/) Selection and peer-review under responsibility of Peer-review under responsibility of the SICE 2018 organizers. Keywords: low-cycle fatigue, thermal-mechanical fatigue, superalloys, cast iron, stainless steels, constitutive equations, damage models 1. Introduction Low Cycle Fatigue of alloys in hot section components occurs in many industrial applications, especially in aero-engines in jet and a rcraft, in aerospace, in powertrain in the automotive industry and in power plants. The design of components experiencing thermal transients and high temperature operation was only at an early stage in the 1980’s. Isothermal low cycle fatigue (LCF) tests on specimens were mostly used since Coffin-Manson law 2nd International Conference on Structural Integrity and Exhibition 2018 Low cycle fatigue of alloys in hot section components: progress in life assessment Luc Rémy* Centre des Matériaux, MINES ParisTech, PSL* Research University, CNRS UMR 7633, BP87, 91003 Evry Cedex, France Abstract Hot section compo ents are exposed to high temperature oper o and thermal transients du ing service life. The research of improved performa ces leads t co si er the risk of crack initiation due to isothermal (LCF) or therm l-mechanical (TMF) low cycl fatigue loading in component design. Thi article gives a sh rt survey of progre s in LCF and TMF life estimation procedures due t the de cription of me allic alloys beh vi r (superalloy , cast iron, stainless ste ls). Assessing the lifetime under cyclic loa ing o ditions requires constitutive models accounting for viscopl sticity t service temperatures or during transients. Thes models can b validated at the laboratory scale using thermal me hanical fatigue tests. Crack initiation lif prediction models ca be quite simple or nee to account fo creep-fatigue interacti ns or nvironme tal effects. Examples illustrate advances in materials studies and models over the years in aero-engine and automotive applications. © 2018 The Authors. Published by Elsevier B.V. This is a open access article under the CC BY-NC-ND lic nse (https://creat vecommons.org/licenses/by- c-nd/4.0/) Selection and peer-review under responsibility of Peer-review under responsibility of the SICE 2018 organizers. Keywords: low-cycle fatigue, thermal-mechanical fatigue, superalloys, cast iron, stainless steels, constitutive equations, damage models 1. Introduction Low Cycle Fa igue of alloys in hot section components occurs in any industrial applications, especially in a ro-engin s in jet and a rcraft, in aerospace, in pow rtrain in the automotive industry and in power plan s. The design of components experien ing thermal transients and high temperature operation wa only at an early tage in the 1980’s. Isothermal low cycle fatigue (LCF) tests on specimens were mostly used since Coffin-Manson law © 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.: +33 1 60 76 30 47; fax: +33 1 60 76 31 50. E-mail address: luc.remy@mines-paristech.fr * Correspon ing author. Tel.: +33 1 60 76 30 47; fax: +33 1 60 76 31 50. E-mail address: luc.remy@mines-paristech.fr

2452-3216 © 2018 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0/) Selection and peer-review under responsibility of Peer-review under responsibility of the SICE 2018 organizers. 2452-3216 © 2018 The Authors. Published by Elsevier B.V. This is a open access article und r the CC BY-NC-ND lic nse (https://creat vecommons.org/licenses/by- c-nd/4.0/) Selection and peer-review under responsibility of Peer-review under responsibility of the SICE 2018 organizers.

* 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  2019 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0/) Selection and peer-review under responsibility of Peer-review under responsibility of the SICE 2018 organizers. 10.1016/j.prostr.2019.05.002