PSI - Issue 2_B

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com ScienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Struc ural Integrity 2 (2016) 2706–2717 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2016) 000–000 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 Multiaxial Fatigue Crack Propagation of an Edge Crack in a Cylindrical Specimen Undergoing Combined Tension-Torsion Loading R.Citarella a , R. Sepe b *, V. Giannella a , I. Ishtyryakov c a Dept. of Industrial Engineering, University of Salerno, via G. Paolo II, 132 - 84084 Fisciano, Italy. b Dept. of Industrial and Information Engineering, Second University of Naples, Via Roma, 29 - 81031 Aversa, Italy. c Kazan Scientific Center of Russian Academy of Sciences, Lobachevsky Street, 2/31 - 420111 Kazan, Russia. Abstract A three-dimensional crack propagation simulation of a hollow cylinder undergoing coupled traction and torsion loading conditions is performed by the Dual Boundary Element Method (DBEM). The maximum tension load and torque are equal to 40 kN and 250 Nm respectively. Specimens, made of Al alloys B95AT and D16T, have been experimentally tested with in-phase constant amplitude loads. The Stress Intensity Factors (SIFs) along the front of an initial part through crack, initiated from the external surface of the hollow cylinder, are calculated by the J-integral approach. The crack path is evaluated by using the Minimum Strain Energy Density (MSED) criterion whereas the Paris’ law, calibrated for the material under analysis, is used to calculate crack growth rates. A cros comparison b tween DBEM and experimental results is presented, showing a good agreement in terms of crack growth rates and paths. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific C mmittee of ECF21. Keywo ds: DBEM; Mixed-M de Crack propagation; Multiaxial fatigue. 1. Introduction Numerical modeling of three-dimensional (3D) fatigue crack growth under mixed mode conditions represents a crucial factor in fracture mechanics in order to assess the residual life of components. The fatigue growth analysis of 21st European Conference on Fracture, ECF21, 20-24 June 2016, Catania, Italy Multiaxial Fatigue Crack ropagation of an Edge Crack in a Cylindrical Specimen Undergoing Combined Tension-Torsion Loading R.Citarella a , R. Sepe b *, V. Giannella a , I. Ishtyryakov c a Dept. of Industrial Engineering, University of Salerno, via G. Paolo II, 132 - 84084 Fisciano, Italy. b Dept. of Industrial nd Information Engineering, Second University of N ples, Via R ma, 29 - 81031 Aversa, Italy. c Kazan Scientific Center of Russian Academy of Sciences, Lobachevsky Street, 2/31 - 420111 Kazan, Russia. Abstract A three-dimensional crack propagati n simulation of a llow cylinder undergoing coupled traction and to sion loading conditions is perform d by the Dual Boundary Element Method (DBEM). The maximum tension load and torqu are equal to 40 kN and 250 Nm r spectively. Specimens, made of Al alloy B95AT and D16T, have been expe i entally test d with in-phas con tant mplitude loads. Th Stress Intensity Factors (SIFs) along the front of an initial p rt through crack, initiated from external surface of the ollow cylinder, are calculated by t J-integr l approach. The crack path is evaluated by using the Minimum Strain Energy D nsity (MSED) criterion whereas the Paris’ law, calibrat d fo the material under analysis, s used to cal ulat crack growth rates. A cross comparison between DBEM and experimental result is pres nted, showing a good agreem nt in terms of crack growth rates and paths. © 2016 The Autho s. Publ shed by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. Keywords: DBEM; Mixed-Mode Crack propagation; Multiaxial fatigue. 1. Introduction Numerical modeling of three-dimensional (3D) fa igu crack growth under mixed mode conditions represents a crucial factor in fracture mechanics in order to assess the residual life of components. The fatigue growth analysis 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.

* Corresponding author. Tel.:+39-081-501-03-18; E-mail address: raffsepe@unina.it * Corresponding author. Tel.:+39-081-501-03-18; E-mail address: raffsepe@unina.it

* 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 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.2016.06.338