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 Struc ural Integrity 5 (2017) 1299–13 3 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

www.elsevier.com/locate/procedia www.elsevier.com/locate/procedia

www.elsevier.com/locate/procedia

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 Paris Law-Based Approach to Fatigue Crack Growth in Notched Plates under Tension Loading Jesús Toribio*, Juan-Carlos Matos, Beatriz González Fracture & Structural Integrity Research Group (FSIRG), University of Salamanca (USAL) E.P.S., Campus Viriato, Avda. Requejo 33, 49022 Zamora, Spain In this paper the crack path is studied for corner and surface flaws emanating from semicircular notch in plates of finite thickness subjected to cyclic tension loading. To this end, a numerical modelin was performed to evaluate the advance of the crack front on the basis of the Paris equation and the stress intensity factor solutions provided by Newman et al . Results show how the growing cracks tend towards a preferential propagation path. The convergence (closeness between crack propagation curves) is faster as the ratio of the notch radius to the plate thickness increases, and also quicker for corner cracks tan for surface flaws. © 2017 The Authors. Publishe by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. Keywords: Corner crack; Surface crack; Plate with a semicircular notch; Fatigue crack propagation; Preferential propagation path 1. Introduction Paris law approaches to fatigue crack g owth in notched pl tes are based on the stress intensity factor (SIF). Solutions were provided by Jergéus (1978), Schijve (1981), Tan et al. (1988), Zhao and Wu (1990), Shivakumar and Newman (1991), Newman et al. (1994), Tan et al. (1996), Lin and Smith (1997) and Wormsen et al . (2006). In the papers by Tan et al. (1988), Shivakumar and Newman (1991), Tan et al . (1996) and Wormsen et al. (2006), the SIF increases with the crack depth and with the ratio of the notch radius to the plate thickness. 2nd International Conference on Structural Integrity, ICSI 2017, 4-7 September 2017, Funchal, Madeira, Portugal Paris Law-Based Approach to Fatigue Crack Growth in Notched Plates under Tension Loading Jesús Toribio*, Juan-Carlos Matos, Beatriz González Fracture & Structural Integrity Research Group (FSIRG), University of al manca (USAL) E.P.S., Campus Viriato, Avda. Requejo 33, 49022 Zamora, Spain Abstract In this paper the rack path is studied for corner a d su face flaws eman ting ro semicirc l r notch in plates of finite thickness subjected to cyclic tension l adi g. To this end, a numeri al m deli g was performed to evaluate the advance f t e crack f nt on the basis of the Paris equatio and the stress intensity fa t r solutions pr vid d y N wman et al . Results show how the g owing crack tend t wards a preferential propagation path. The convergence (closeness b tween cr ck p opag tion curves) is faster as the ratio of the notch radius to the plate thickness increases, and also quicker for corner cracks tan for surface flaws. © 2017 The Autho s. Publ shed by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. Keywords: Corner crack; Surface crack; Plate with a semicircular notch; Fatigue crack propagation; Preferential propagation path 1. Introduction Paris la ap r aches to fatig e crack growth in notched pla es are based on the stress intensity f ctor (SIF). Solutions w re provided by Jergéus (1978), Schijve (1981), Tan et al. (1988), Zhao and Wu (1990), Shivakumar and Newman (1991), N wman et al. (1994), Tan et al. (1996), Lin and Smith (1 97) and Wormsen et al . (2 06). In the pap rs by Tan et al. (1988), Shivakumar and Newman (1991), Tan et al . (1996) and Wormsen et al. (2006), the SIF increases with the crack depth and with the ratio of the notch radius to the plate thickness. © 2017 The Authors. Published by Elsevier B.V. Peer-review under 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

* Corresponding author. Tel.: +34-980-545000; fax: +34-980-545002 E-mail address: toribio@usal.es * Correspon ing author. Tel.: +34-980-545000; fax: +34-980-545002 E-mail address: toribio@usal.es

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.2017.07.115 * 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.