PSI - Issue 5

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at www.sciencedire t.com ScienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 P o edia Structural Int gr ty 5 7 5–12 Available online at www.sciencedirect.com 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. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017 Novel test prototype for the determination of mode I fracture parameters: application to adhesively bonded electronics. Lassaad Ben Fekih a *, Olivier Verlinden a , Christophe De Fruytier b , Georges Kouroussis a a University of Mons, 20 Place du Parc, 7000 Mons, Belgium b Thales Alenia Space, Rue Chapelle Beaussart, 6032 Mont-Sur-Marchienne, Belgium Abstract Structural adh sives are common y used i space electronics particularly for bonding ceramic quad flat packages t printed circuit boards (PCB). In such application, adhesive joints are subjected to high loads due to the PCB bending under severe acceleration of the launch. It is thus mandatory to figure out the adhesive mechanical resistance in order to achieve a safe design. The present paper is concerned with the determination of the cohesive properties of an aerospace adhesive in tensile fracture mode. For this purpose, a novel test prototype consisting of a ceramic component adhesively bonded to a PCB plate is designed and tested subsequently in quasi-static loading. In parallel, a finite element (FE) model of the assembly is developed using ABAQUS software. The adhesive joint is modelled by user defined cohesive elements. The latter are implemented using a FORTRAN user subroutine (UEL) capable of simulating the ge metrical and material nonlinearities of the adhesive. A good ag eem nt is obtained between experimental and numerical results after updating. This inding permitted to succ sfully find out the cohesive parameters of the tested dhe ive. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. 2nd International Conference on Structural Integrity, ICSI 2017, 4-7 September 2017, Funchal, Madeira, Portugal Novel t st prototype for the determination of mode I fracture parameters: application to adhesively bonded electronics. Lassaad Ben Fekih a *, Olivier Verlinden a , Christophe De Fruytier b , Georges Kouroussis a a University of Mons, 20 Pl ce du Parc, 7000 Mons, Belgium b Thales Alenia Space, Rue Chapelle Beaussart, 6032 Mont-Sur-Marchienne, Belgium Abstract Structural adhesives are commonly used in space electronics particularly for bonding ceramic quad flat packages to printed circuit boards (PCB). In such application, adhesive joints are subjected to high loads due to the PCB bending under severe acceleration of the launch. It is thus mandatory to figure out the adhesive mechanical resistance in order to achieve a safe design. The present paper is concerned with the determination of the cohesive properties of an aerospace adhesive in tensile fracture mode. For this purpose, a novel test prototype consisting of a ceramic component adhesively bonded to a PCB plate is designed and tested subsequently in quasi-static loading. In parallel, a finite element (FE) model of the assembly is developed using ABAQUS software. The adhesive joint is modelled by user defined cohesive elements. The latter are implemented using a FORTRAN user subroutine (UEL) capable of simulating the geometrical and material nonlinearities of the adhesive. A good agreement is obtained between experimental and numerical results after updating. This finding permitted to successfully find out the cohesive paramet rs of the tested adhesiv . © 2017 The Au hors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committe of ICSI 2017. 2nd International Conference on Structural Integrity, ICSI 2017, 4-7 September 2017, Funchal, Madeira, Portugal

© 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Keywords: Fracture analysis, numerical modelling Keywords: Fracture analysis, numerical modelling

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

* Corresponding author. Tel.: +32 65 37 42 16; fax: +32 65 37 41 83. E-mail address: lassaad.benfekih@umons.ac.be * Corresponding author. Tel.: +32 65 37 42 16; fax: +32 65 37 41 83. E-mail address: lassaad.benfekih@umons.ac.be

2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. 2452-3216  2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017 10.1016/j.prostr.2017.07.051 * Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt 2452-3216 © 2017 Th Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. 2452-3216 © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017.