PSI - Issue 5

ScienceDirect Available online at www.sciencedirect.com Available online at www.sciencedirect.com Sci ceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 5 (2017) 286–293 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 Evaluation of rotational deformation in compact specimens for CTOD fracture toughness testing Yoichi Kayamori a, *, Tomoya Kawabata b a Steel Research Laboratories, Nippon Steel & Sumitomo Metal Corporation,1-8 Fuso-cho, Amagasaki, Hyogo, 660-0891 Japan b Department of Systems Innovation, The University of Tokyo, 7-3-1 Hongo Bunkyo-ku, Tokyo, 113-8656 Japan Abstract In Crack Tip Opening Displacement (CTOD) fracture toughness tests, the plastic hinge model is used for calculating the plastic component of CTOD, but the accuracy of the plastic hinge model has been a matter of controversy. In this study, 3-D elastic-plastic finite element analysis was conducted by using a stepped notch 1T compact specimen model, in which the ratio of crack length to specimen was set at 0.5. Two steel models, the low yield to tensile ratio, Y/T , of 0.6 and the high Y/T of 0.9, were employed for the analysis. The plastic rotational center was determined by using distributions of the plastic strain increment and the total strain increment in the crack opening direction along the ligament on the mid-thickness plane. The effect of Y/T on the plastic rotational factor was quite small in the C(T) specimen model, and the average of their plastic rotational factors was 0.52 in both Y/T steel models. This plastic rotational factor is consistent with conventional ones, and is reasonably used for CTOD calculation. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific C mmittee of ICSI 2017. Keywo ds: CTOD ; Plastic hinge model ; Plastic rot tional factor ; Compact specimen ; Yield to tensile ratio ; Finite element analysis 2nd International Conference on Structural Integrity, ICSI 2017, 4-7 September 2017, Funchal, Madeira, Portugal Eval ation of rotational deformation in compact specimens for CTOD fracture toughness testing Yoichi Kayamori a, *, Tomoya Kawabata b a Steel Research Laboratories, Nippon Steel & Sumitomo Metal Corporation,1-8 Fuso-cho, Amagasaki, Hyogo, 60-0891 Japan b Department of Systems Innovation, The University of Tokyo, 7-3-1 Hongo Bunkyo-ku, Tokyo, 113-8656 Japan Abstract In Cr ck Tip O e i g Displacemen (CTOD) fracture toughness tests, the plastic hi ge od l is used f r calculating the plastic component of CTOD, but the accuracy of the plastic hinge model has been a matter of ontroversy. In this study, 3-D las c-plasti finite element analysis wa conducted by using a stepped notch 1T compact p cimen model, in which the ratio of crack length to s ecimen was set t 0.5. wo steel models, the low yield to t nsile ratio, Y/T , of 0.6 and the high Y/T of 0.9, were employed for analy is. The plastic rotational center was determ ned by using distributi ns of the plastic strain i crem nt and the total strain increment in the crack opening direction along the ligament on th mid-thickness plane. The effect of Y/T on the plastic rotational factor was quite small in the C(T) spec men model, and the average of their plastic rotational fact rs was 0.52 in both Y/T steel models. This plastic rotational factor is consistent with conventional ones, and is reasonably used for CTOD calculation. © 2017 The Autho s. Publ shed by Elsevier B.V. Peer-review under responsibility of he Sci ntific Committee of ICSI 2017. Keywords: CTOD ; Plastic hinge model ; Plast rotational factor ; Compact specim n ; Yield to tensile ratio ; Finite element analysis © 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.

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.2017.07.135 * 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. * Corresponding author. Tel.: +81-6-7670-8745; fax: +81-6-6489-5794. E-mail address: kayamori.k9k.yoichi@jp.nssmc.com * Corresponding author. Tel.: +81-6-7670-8745; fax: +81-6-6489-5794. E-mail address: kayamori.k9k.yoichi@jp.nssmc.com