PSI - Issue 5

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 5 (2017) 883–888 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. 2nd International Conference on Structural Integrity, ICSI 2017, 4-7 September 2017, Funchal, Madeira, Portugal A Generalization of Neuber’s Rule for Numerical Applications Daniel Kujawski a, *, Joshua LK Teo b a Western Michigan University, Mechanical and Aerospace Engineering, Kalamazoo MI, 49008, U.S.A. b Western Michigan University, Mechanical and Aerospace Engineering, Kalamazoo MI, 49008, U.S.A In this paper, a generaliz ation of Neuber’s rule for a quick and easy elastic/plastic notch analysis is established and discussed. The proposed generalization allows for a numerical and/or graphical solution for any notch geometry as well as its associated stress concentration factor, k t , and fatigue notch factor, k f . It is shown that the so called Neuber’s “master” curve, involved in such analy is, is unique and is only material dependent. This is obtained by a simultaneous solution of the Ramberg-Osgood relationship and Neuber’s r ule. These solutions are plotted in terms of the product of nominal stress, S, times stress concentration factor, k t (or k f ), versus the actual notch root strain,  . The Neuber’s “master” curve can be interactive and is applicable for both monotonic and cyclic loading situations. The present formulation is pertinent to conditions when applied nominal stresses, S , is below material’s yield stress,  0 , i.e.  S  0 . The proposed method is particularly suitable for rapid fatigue life predictions and material screening during pre-prototype phase of notched component design. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. Keywords: Neuber’s rule; notch analysis; Neuber’s “master” curve 1. Introduction Fracture of components usually initiates at the stress concentrations or so called hot-spots, where local stresses and strains are higher than nominal ones and often exceed yielding. Therefore, it is important to accurately estimate the local elastic-plastic stresses and strains at notches or hot-spots. While elastic-plastic finite element analysis 2nd International Conference on Structural Integrity, ICSI 2017, 4-7 September 2017, Funchal, Madeira, Portugal A Generalization of Neuber’s Rule for Numerical Applicati ns Daniel Kujawski a, *, Joshua LK Teo b a t i i i it , i l Aerospace Engineering, Kalamazoo MI, 49008, U.S.A. b Western Michigan University, Mechanical and Aerospace Engineering, Kalamazoo MI, 49008, U.S.A Abstract In this paper, a generaliz ati n of Neuber’s rule for a quick and easy elastic/plastic notch analysis is e tablished and discussed. The proposed ge eralization allows for numerical and/or graphical solution for any notch geometry as well as its associated stress concentration factor, k t , and f tigue notch factor, k f . It is shown that the so called Neuber’s “master” curve, involve in such analysis, is nique and is only material dependent. This is obtained by a simultaneous solution of the Ramberg-Osgo d relationship and Neuber’s r ule. These solutions re plotted in terms of the product of nominal stress, S, times stress oncentrati n factor, k t (or k f ), versus the actual notch root strain,  . The Neuber’s “mast r” curve can be int ractive and is applicable for both monotonic nd cyclic loading situations. The present formulation is pertinent to conditions when applied nominal stresses, S , is below material’s yield stress,  0 , i.e.  S  0 . The proposed method is particularly suitable for rapid fatigue life predictions and material screening during pre-prototype phase of notched component design. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. Keywords: Neuber’s rule; notch analysis; Neuber’s “master” curve 1. Introduction Fractur of components usually initiat s at the stress c ncentrations or so called hot-spots, where local stresses and strains are higher than nominal ones and often exceed yielding. Therefore, it is important to accurately estimate the local elastic-plastic stresses and strains at notches or hot-spots. While elastic-plastic finite element analysis © 2017 Th Authors. P blished by Elsevier B.V. Peer-review und r responsibility of the Scientific Committee of ICSI 2017 © 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

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.2017.07.116 * 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. * Correspon ing author. Tel.: +1-269-276-3428; fax: +1-269-276-3421. E-mail address: daniel.kujawski@wmich.edu * Corresponding author. Tel.: +1-269-276-3428; fax: +1-269-276-3421. E-mail address: daniel.kujawski@wmich.edu