PSI - Issue 2_A

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com ienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Struc ural Integrity 2 (2016) 1451–1456 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2016) 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. 21st European Conference on Fracture, ECF21, 20-24 June 2016, Catania, Italy Design and characterization of a small-scale solar sail deployed by NiTi Shape Memory actuators Girolamo Costanza a* , Maria Elisa Tata a a Dipartimento di Ingegneria Industriale, Università di Roma-Tor Vergata, Via del Politecnico 1, 00133 Roma - Italy Abstract Solar sails exploit the radiation pressure as propulsion system for the exploration of the solar system. Sunlight is used to propel space vehicles by reflecting solar photons from a large and light-weight material, so that no propellant is required for primary propulsion. Kapton seems to be the most suitable material for the sail production and in the space missions till now activated booms as deployment systems have always been used. In this work a self deploying system based on NiTi Shape Memory wires has been designed and manufactured in a small-scale prototype. As kapton has always been employed with a thin Al coating on one or both surfaces of the sail, for the first experiments commercial pure Al thin sheets have been used in order to simulate the sail. In the small-scale prototype manufactured, three different configurations have been studied for bending the sail while two different Nitinol wires have been used as active materials for the self-deployment of the sail. Infrared lamps have been employed in order to warm the solar sail and obtain the activation of the shape memory active elements. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. Keywords: Solar sail, Shape memory Alloy, Self-deployment systems. 1. Introduction Solar sails exploit the light of the sun as propulsion system (Gregorio et al.). According to this relatively novel propulsion system no chemical propellant is necessary for imparting motion in the space. The basic concept of solar sailing is thus the use of quantum packets of energy (solar radiation pressure) to propel a spacecraft potentially providing a continuous acceleration limited only by the lifetime of sail aterial in the space environments (Tsuda et al. 2011). A great number of photon in the sunshine light interacts with the solar sail and produces a small radiation pressure on the sail itself (Leipold et al. 2003, Colin et al. 2004). For this reason, in order to exploit this propulsion system, a great surface of the sail is required, and materials employed for the construction of the sail must be lightweight and high reflectivity (Block et al. 2011). Ion propulsion engines for small satellites are based on the © h P Copyright © 2016 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (http://creativec mmons.org/licenses/by-nc-nd/4.0/). Peer-review und r responsibility of the Scientific Committee of ECF21. © 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 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21.

2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Copyright © 2016 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license ( http://creativecommons.org/licenses/by-nc-nd/4.0/ ). Peer review under responsibility of the Scientific Committee of ECF21. 10.1016/j.prostr.2016.06.184