PSI - Issue 3

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com ienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 P o edi Structural Integr ty 3 (2017) 41–47 Available online at www.sciencedirect.com Scie eDirect 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. Copyright © 2017 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 IGF Ex-Co. XXIV Italian Group of Fracture Conference, 1-3 March 2017, Urbino, Italy Failure nalysis of a diesel engine J.L. González a , D. Rivas a , M.A. Beltrán b * a Professor of the Metallurgy and Materials Department, ESIQIE IPN, México, D.F. b PhD student of the Metallurgy and Materials Department, ESIQIE IPN, México, D.F Abstract This paper presents the failure analysis of a diesel engine with 16 cylinders in V and 592 liters of displacement that was used for electric power generation, which failed at 27,000 hours of service. The study was performed by visual inspection and macroscopic examination of fractured elements, from which it was determined that the origin of the failure was the fracture by fatigue of one of the four B3 cylinder crown bolts whose fracture propitiated the failure of the other three bolts, so that the crown fell into the cylinder combustion chamber blocking the displacement of the piston, generating the buckling and fracture of the piston rod. The chemical composition, Brinell hardness and microstructural analysis of the crown bolts determined that the fatigue of the B3 cylinder crown bolt was due to an excessive tightening torque during its installation process which generated high stresses that, together with a lower fatigue strength caused by a slightly lower hardness in the failed bolt, produced the crown bolt fracture. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of IGF Ex-Co. Keywords: failure analysis; diesel engine; fracture mechanics. 1. Introduction A iesel engine of 16 cylinders in V a d 592 liters of displacemen that was used for generation of electrical power failed to the 27,000 hours of service; according to the maintenance history, the services of the 1,500, 3,000 and 7,000 hours were made according to the manufacturer's recommendations. The engine failed shortly before the overhaul service it would receive by completing the 30,000 service hours. XXIV Italian Group of Fracture Conference, 1-3 March 2017, Urbino, Italy Failure analysis of a diesel engine J.L. González a , D. Rivas a , M.A. Beltrán b * a Professor of the Metallurgy and Materials Department, ESIQIE IPN, México, D.F. b PhD student of the Metallurgy and Materials Department, ESIQIE IPN, México, D.F Abstract This paper resents the failure nalysis of a die el engine with 16 ylinders in V and 592 liters of displacement that was used for electric power generation, which failed at 27,000 hours of service. The study was performed by visual inspection and m croscopic examination of fractured elements, from which it was determined that the origin of the failure was the fracture by fatigue of one of the four B3 cylinder c own bolts whose fracture propitiated the failure of the other thre bo ts, so that the crown fell into the cylinder comb stion chamber blocking the di placement of the piston, gene ating the buckling and fracture of the piston rod. The chemical po ition, Brinell hardness and microstructural analysis of the c own bolts determined th t he fatigu of he B3 cylinder crown b lt was due to an excessive tightening torque duri g its installati n proce s which g ner ted high str sses that, togeth with a l wer fatig e stre gth caused by a sl ghtly lower hardne s in the failed b lt, produ ed the crown bolt fracture. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of IGF Ex-Co. Keywords: failure analysis; diesel engine; fracture mechanics. 1. Introduction A diesel ngine of 16 cylinders in V and 592 liters of displacement that was used for gen ration of electrical power failed to the 27,000 hours of service; a cording to the ma ntena ce his ory, the services of the 1,500, 3,000 and 7,000 hours wer made acc rding to the manufacturer's r comm dations. The engine failed s ortly before the overhaul service it woul receive by completing the 30,000 s rvice hours. © 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 © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of IGF Ex-Co. 2452-3216 © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of IGF Ex-Co. * Corresponding author. Tel.: +52-55-57296000 ext. 54264; fax: 54267. E-mail address: mabz_2205 @ hotmail.com * Corresponding author. Tel.: +52-55-57296000 ext. 54264; fax: 54267. E-mail address: mabz_2205 @ hotmail.com

2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Copyright © 2017 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 IGF Ex-Co. 10.1016/j.prostr.2017.04.007