PSI - Issue 13

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at www.sciencedire t.com ienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 13 (2018) 741–745 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2018) 000 – 000 Available online at www.sciencedirect.com ScienceDirect Structural I tegrity 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. ECF22 - Loading and Environmental effects on Structural Integrity Microstructural and numerical analysis of fracture mechanisms in a thermal barrier coating system on Ni-based superalloys Elena Fedorova a,b *, Andrey Burov b , Nadezhda Sukhodoeva a , Vladim r Moskvichev b a Siberian Federal University, Krasnoyarsk 660041, Russia b Institute of Computational Technologies SB RAS, Krasnoyarsk Branch Office, Krasnoyarsk 660049, Russia The numerical analysis of factors governing the magnitude and distribution of residual thermal stress in an oxide/metal system was carried out regarding industrial applications of Ni-based superalloys protected with the thermal barrier coating system (TBC). The particular emphasis was paid on the microstructural characterization of damaging behavior of the α -Al 2 O 3 thermally grown oxide (TGO) and the integrity along the TGO/NiCoCrAlY-bond coat and TGO/ZrO 2 -Y 2 O 3 top coat interfaces which are the key to successful application of TBC systems. The cross-sections of samples after the high temperature cyclic oxidation tests at 1100  C in air were characterised by SEM-EDS to study the fracture mechanisms and to model the TBC system. The data on the TGO thickness, its uniformity, chemical and phase compositions, spallation occurrence, and geometry of the interfaces were obtained. The numerical analysis of residual thermal stress was run for five different cooling rates using a finite element model. The following parameters influencing the stress state developed during cooling from the oxidation temperature were considered: physical and mechanical properties of the components, geometry of the interface including roughness and thickness. All the material layers were assumed to creep at elevated temperature. Finally results have been discussed in relation with creep mechanisms for TBCs layer. © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. Keywo ds: Ni-bas syperall y; TBC; interface; residual thermal tres ; FEM © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. ECF22 - Loading and Environmental effects on Structural Integrity Microstructural and numerical analysis of fracture mechanisms in a thermal barrier coating system on Ni-based superalloys Elena Fedorova a,b *, Andrey Burov b , Nadezhda Sukhodoeva a , Vladimir Moskvichev b a Siberian Federal University, Krasnoyarsk 660041, Russia b Institute of Computational T ch ologies SB RAS, Krasnoyarsk Branch Office, Kr snoyarsk 660049, Russia Abstract The numerical analysis of factors governing the magnitude and distribution of residual thermal stress in an oxide/metal system was carried out regarding industrial pplications of Ni-based superalloys protected with th t ermal barrier coating ystem (TBC). The p rticular emphasis was paid on the microstructural charact rization of damaging behavior of the α -Al 2 O 3 thermally grown oxid (TGO) and the integrity along the TGO/NiCoCrAlY-bond co t a d TGO/ZrO 2 -Y 2 O 3 t p coat interfaces which are the key to successful application of TBC syst ms. The cross-sections of samples after the high temperature cyclic oxidation tests at 1100  C in air were characterised by SEM-EDS to study the fracture mechanisms and to model the TBC system. The data on the TGO thickness, its uniformity, chemical and phase compositions, spallatio occurrence, and geom try of the interfaces were obtain d. The numerical analysis of residual thermal stress was run for five different cooling r tes using a finite lement model. The following parameters influencing the stress state developed during cooling from the oxidation temperature were considered: physical a d mechanical prop rties of the components, geometry of the interface including roughness and thickness. All the material layers were assumed to creep at elevated temp rature. Finally results have be n discussed in relation with cr ep mechanisms for TBCs layer. © 2018 The Authors. Published by Elsevier B.V. Peer-review und r responsibility of the ECF22 organizers. Keywords: Ni-based syperalloy; TBC; interface; r idua t ermal stress; FEM © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. 1. Introduction Thermal barrier coatings (TBC) are widely used to protect the hot section structural components, such as aircraft gas turbine engines and industrial gas turbines, against oxidation and large thermal gradients during service life. Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation. Thermal barrier coatings (TBC) are widely used to protect the hot section structural components, such as aircraft gas turbine engines and industrial gas turbines, against oxidation and large thermal gradients during service life. Abstract 1. Introduction

* Corresponding author. Tel.: +7-913-532-7455. E-mail address: efedorova@sfu-kras.ru * Corresponding author. Tel.: +7-913-532-7455. E-mail ad ress: efedorova@sfu-kras.ru

* 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.

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.2018.12.123