PSI - Issue 2_B

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com Sci ceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Struc ural Integrity 2 (2016) 2566–2574 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 Validati n of c tour integral functions ( J and C ( t )) in ABAQUS v6.11-v6.14 for combined mechanical and residual stresses Yuebao Lei a * a EDF Energy Nuclear Generation Ltd., Barnett Way, Barnwood, Gloucester, GL4 3RS, UK Abstract Theoretical and numerical validations are performed for the ABAQUS contour integral J and C ( t ) functions in its versions v6.11 14 for cases with residual stresses. Test cases are specially designed to introduce various residual stress types followed by cracked-body fracture/creep analyses. Crack driving force parameters J and C ( t ) are evaluated using both the inbuilt contour integral functions in ABAQUS v6.14 and self-developed software. Based on the results, guidance is developed for users to obtain correct J and C ( t ) values using ABAQUS v6.11-14. © 2016 The Authors. Published by Elsevier B.V. Pe r-r view under res on ibili y of the Scientific Committee of ECF21. Keywords: ABAQUS; J calculation; C ( t ) calculat on; residual stresses; contour integral 1. Introduction Crack driving force parameters, such as the J -integral for fracture and C ( t ) for creep crack growth, where t is time, evaluated using the commercial finite element (FE) code ABAQUS (see ABAQUS (2010), (2014)), are widely used in fracture mechanics research and the structural integrity assessment of plant components. Therefore, the reliability of fractu mechan cs paramet rs evaluated from FE analyses using ABAQUS is very important. In the early versions of ABAQUS (v6.10 and lower (ABAQUS (2010))), the Rice J definition (Rice (1968)) with corrections for thermal loading was incorporated, which is path-dependent for general residual stress problems. The line integral given by Bassani and McClintock (1981) was incorporated for evaluating C ( t ). From version v6.11 and 21st European Conference on Fracture, ECF21, 20-24 June 2016, Catania, Italy Validation of contour integral functions ( J and C ( t )) in ABAQUS v6.11-v6.14 for combined mechanical and residual stresses Yuebao Lei a * a EDF Energy Nuclear Generation Ltd., Barnett Way, Barnwood, Gloucester, GL4 3RS, UK Abstract Theoretical and numerical validations are performed for the ABAQUS contour integral J and C ( t ) functions in its versions v6.11 14 f r cases with r s dual stresses. Test cases are specially designed to introduce various residual stress types followed by cracked-body fracture/creep analy es. Cra k driving force parameters J and C ( t ) are eval ated using both the inbuilt contour integral functions in ABAQUS v6.14 and self- e eloped software. Based o the results, guid nce is devel ped for users to b ain correct J a d C ( t ) values using ABAQUS v6.11-14. © 2016 The Au hors. Published by Elsevier B.V. Peer- eview under respons bility of the Scientific Com ittee of ECF21. Keywo ds: ABAQUS; J calculat on; C ( t ) calculation; residual stresses; contour integral 1. Introduction Crack driving force parameters, such as the J -integral for fracture and C ( t ) for creep crack growth, where t is ti e, evaluat d using the commercial finite element (FE) code ABAQUS (see ABAQUS (2010), (2014)), are widely used in fracture mechanics research and the structural integrity assessment of plant components. Therefore, the reliab lity of fractu mechanic parameters evaluated from FE analyses using ABAQUS is very important. In th early versions of ABAQUS (v6.10 and lower (ABAQUS (2010))), the Rice J definition (Rice (1968)) with corrections for thermal l ading was incorpor ted, hich is path-dependent for general residual stress problems. The line integral given by Bassani and McClintock (1981) was incorporate for evaluating C ( t ). From version v6.11 and 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.: +44-1452652285 E-mail address: yuebao.lei@edf-energy.com * Corresponding author. Tel.: +44-1452652285 E-mail ad ress: yuebao.lei@edf energy.com

* Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt 2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review und r responsibil ty of the Scientific Committee of ECF21. 2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer review under r sponsibility 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.2016.06.321