PSI - Issue 2_B

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 Structu al Integrity 2 (2016) 309–315 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 The Partitioning of Plastic Energy in Cutting Tests L. Chang a , Y. Patel b , H.Wang a , J.G. Williams a, b * a School of Aerospace, Mechanical and Mechatronic Engineering,University of Sydney, Sydney, NSW 2006, Australia b Mechancial Engineering Department, Imperial College London, South Kensington Campus, London SW7 2AZ, UK Cutting analyses incorporating chip bending in addition to shear yielding and fracture toughness have been presented. A plastic bending term (e b /γ)(h c /h) is included which corrects the yield stress, σ Y , determined from the cutting data. The experimental data for seven polyme s derived from measuring both the chip thickness and the resi ual radius of curvature show that the contribution of bending is up to about 12%. This gives a correction to σ Y of about the same order but G c is unaffected as (e b /γ)(h c /h) is a factor independent of the cutting depth. The corrected σ Y values are compared with the σ Y values in simple compression and it suggests a work hardening effect for the polyolefines. Also, the low bending strain in the chips of HMWPE and PP may be attributed their large degree of non-linearity observed in the compression test. © 2016 L. Chang, Y. Patel, H. Wang and J.G. Wiliiams. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. Keywords: cutting, chip bending, fracture toughness, polymers, work h rdening 1. Introduction Orthogonal cutting tests have been employed in the determination of the fracture toughness of polymers [1]. Sharp tools with an angle θ are used to cut surface layers of varying thickness, h, and the cutting force F c and transve se force F t are measured as show in Fig. 1 (a). As drawn in Fig. 1, the deformation mode in the chip is bending and for large radii of curvature the deformation is elastic giving no plastic deformation and hence no energy dissipation. On unloading the chip would be straight. For larger angles and smaller thicknesses, the radius of 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. © 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. Abstract

* Corresponding author. Tel.: +44 (0)20 7594 7200 E-mail address: g.williams@imperial.ac.uk

* 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.2016.06.040