PSI - Issue 13

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com cienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structural Integrity 13 (2018) 1043–1 46 Available online at www.sciencedirect.com ScienceDirect StructuralIntegrity Procedia 00 (2018) 000–000 ScienceDirect StructuralIntegrity Procedia 00 (2018) 000–000

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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. ECF22 - Loading and Environmental effects on Structural Integrity Numerical Simulation of Spall Behavior of Metal Under Strong Impact Loading Zheng Miao, Yu Xin, Yin JianWei* Institute of Applied Physics and Computational Mathematics, Beijing, 100094, China Abstract When the metal material undergo complex loading processes, such as strong impact loading, unloading, backward drawing and reloading, they are likely to spall in the reverse tension stage. In this paper, the following four items are considered in the modeling of material spallation: ① the damage variable in the spallation modeling adopts the concept of porosity; ② the equation of state containing hole material is calculated by the solid component in the damage unit; ③ when the porosity of the unit reaches the critical porosity, it is considered that the por s are interpenetrat d with each other to form macr crack, and the material is fractured as a whole; ④ When the macr fracture unit is compressed again, if the averag compression ratio of the unit reaches the closed critical value, it is considered that the unit is compressed into holed hole. In the existing the two dimension Lagrange fluid dynamics program, we have added the hole fracture growth, polymerization and collapse effect of spallation processing function, and verify the model and pr gram code through a numerical example. The damage volution analysis of the unit near a single measuring poin shows that t e platf rm area in the velocity curve corr sponds to the da age fracture zone in the metal. It is consid re that the unit of the location has und rgo the physical process of unl ad-stretching-damage fracture-free flight- recompression. ECF22 - Loading and Environmental effects on Structural Integrity Numerical Simulation of Spall Behavior of Metal Under Strong Impact Loading Zheng Miao, Yu Xin, Y JianWei* Institute of Applied Physics and Computational Mathematics, Beijing, 100094, China Abstract When the metal material undergo complex loading processes, such as strong impact loading, unloading, backward drawing and reloading, they are likely to spall in th reverse tension stage. In this paper, the followi g four items are considered in the modeling of material spallation: ① the damage variable in the spallation modeling a opts the conc pt of porosi y; ② the equation of s ate containing hole m terial is ca culated by the solid component in the da ag u it; ③ when the orosity of unit reaches the critical porosity, it is considered ha the por s are interpenetrated with each other to form macro crack, and the materi l is fractured as a whole; ④ When the macro fracture unit is compressed again, if the average c mpression ratio of th unit reaches the closed critical value, is considered that the unit is compressed into holed hole. In t e existing the two dimension Lagrange fluid dynamics program, we h ve added the hol fracture growth, polymerization and co lapse effect of spallation processing function, and verify the model an program code through a numerical example. The damage evolution analysis of the unit near a single measuring point shows that the platform area in the velocity curve corresponds to the damage fracture zone in the metal. It is considered that the unit of the location has undergo the physical process of unload-stretching-damage fracture-free flight- recompression.

© 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. © 2018 The Authors. Published by Elsevier B.V. Peer-review under re ponsibility of the ECF22 organizers. © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. Keywords: Spall; Simulation; Metal Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation.

Keywords: Spall; Simulation; Metal

* Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt 2452-3216© 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. 2452-3216© 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers.

2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016.

2452-3216  2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. 10.1016/j.prostr.2018.12.195