PSI- Issue 9

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedirect.com cienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 9 (2018) 295–302 Available online at www.sciencedirect.com ScienceDirect Structural Int grity Procedia 00 (2018) 000–000 Available online at www.sciencedirect.com ScienceDirect Structural Integrity 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 Gruppo Italiano Frattura (IGF) ExCo. IGF Workshop “Fracture and Structural Integrity” Fracture behaviour of alloys for a new laser ranged satellite F. Felli a *, A. Brotzu , D. Pilone a , A. Paolozzi b and I. Ciufolini c, d a DICMA, Sapienza Università di Roma, Roma b Scuola Ingegneria Aerospaziale, Sapienza Università di Roma, Roma c Dip. Ingegneria dell’innovazione, Università del Salento, Lecce d Centro Fermi, Roma Abstract A new laser-ranged satellite called LARES 2 (Laser Relativity Satellite 2) has been recently designed for accurate tests of Einsten’s theory of General Relativity and space geodesy. Some high density alloys (8.6-9.3 g/dm3) have been studied and characterised for producing the LARES 2 passive satellite. The considered materials were Copper and Nickel based alloys that have been produced and characterised. Aim of this work was to analyse their fracture behaviour that is a requirement for materials to be used for space applications. Fracture tests have been carried out on several specimens and fracture surfaces have been analysed. © 2018 The Authors. Published by Elsevier B.V. Peer- eview under responsibility of the Gruppo Italian Frattura (IGF) ExCo. Keywords: C pper all ys ; Lares 2; material selection. 1. Introduction LARES 2 is a passive las r-ranged s t llite designed and developed for tests of Einstein’s theory of General Relativity and space-geodesy (Ciufolini et al. (2017 , 2017b and 2017c)). In par icular LARES 2 will provide the most accurate measurement of frame-dragging or Lense-Thirring effect (Ciufolini (2007)), a fundamental and intriguing phenomenon predicted by General Relativity with basic astrophysical application such as the generation of gravitational waves by two colliding black holes measured by the LIGO laser interferometers. A basic requirement in designing LARES 2 is the minimization of its cross-section-to-mass ratio to reduce as much as possible its orbital IGF Workshop “Fracture and Structural Integrity” Fracture behaviour of alloys for a new laser ranged satellite F. Felli a *, A. Brotzu a , D. Pilone a , A. Paolozzi b and I. Ciufolini c, d a DICMA, Sapien Università di Roma, Roma b Scuola A rospazi le, Sapie za Università di R ma, Roma c Dip. Ingegneria dell’innov zione, Università del Salento, Lecce d Centro Fermi, Roma Abstract A new laser-ranged satellite called LARES 2 (Laser Relativity Satellite 2) has been recently designed for accurate tests of Einsten’s theory of General elativity and space geodesy. Som high density alloys (8.6-9.3 g/dm3) have been studied and characterised for producing the LARES 2 passive satellite. The considered materials were Copper and Nickel based alloys that hav been produced nd characterised. Aim of t is work was to analyse their fracture behaviour th t is a requirement for materials to be used for space applications. Fracture tests have been carried out on several specimens and fracture surfaces have been analysed. © 2018 The Authors. Published by Elsevier B.V. Pe r-r view under res on ibili y of the Gruppo Italiano Frattura (IGF) ExCo. Keywords: Copper all ys ; Lares 2; material selection. 1. Introduction LARES 2 is a passive laser-ranged satellite designed and developed for tests of Einstein’s theory of General Relativity and space-geodesy (Ciufolini et al. (2017a, 2017b and 2017c)). In particular LARES 2 will provide the most accurate measurement of frame-dragging or Lense-Thirring effect (Ciufolini (2007)), a fundamental and intriguing phenomenon pr dicted by General Rela vity with basic astrophysical application such as the generation of gravitational waves by two colliding black holes measured by the LIGO laser interferometers. A basic requirement in designing LARES 2 is the minimization of its cross-section-to-mass ratio to reduce as much as possible its orbital © 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.: +390644585601. E-mail address: Ferdinando.felli@uniroma1.it * Correspon ing author. Tel.: +39064458560 . E-mail address: Ferdinando.felli@uniroma1.it

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 Gruppo Italiano Frattura (IGF) ExCo. 10.1016/j.prostr.2018.06.026 * Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt 2452 3216 © 2018 Th Authors. Published by Elsevier B.V. Peer-review under responsibility of the Gruppo Italiano Frattura (IGF) ExCo. 2452-3216 © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Gruppo Italiano Frattura (IGF) ExCo.