PSI - Issue 7

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at www.sciencedire t.com ScienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 7 (2017) 46 –467 Available online at www.sciencedirect.com ScienceDirect Structural I tegrity 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. 3 rd International Symposium on Fatigue Design and Material Defects, FDMD 2017, 19-22 September 2017, Lecco, Italy Quantitative Evaluation of the Flaking Strength of Rolling Bearings with Small Defects (Part 2: Evaluation of th Flaking Strength of Rolling Bearings with Small Drilled Holes, based on th Stress Intensity Factor) Hisao Matsunag a,b,c , Sho Hashimoto d,e, *, Hiroki Komata e , a Kyushu U iv. Faculty of Engi eering, 744 M tooka, Nishi-ku, Fukuoka-shi, Fukuoka, 819-0395 Japan b Kyushu Univ. International Institute for Carbon-Neutral Energy Research (I2CNER), 744 Motooka, Nishi-ku, Fukuoka-shi, Fukuoka , 819-0395 Japan c Kyushu Univ. Research Center for Hydrogen Industrial Use and Storage (HYDROGENIUS), 744 Motooka, Nishi-ku, Fukuoka-shi, Fukuoka, 819-0395 Japan d Kyushu Univ. Graduate School of Engineering, 744 Motooka, Nishi-ku, Fukuoka-shi, Fukuoka, 819-0395 Japan e Core Technology R&D Center, NSK Ltd., 1-5-50 Kugenumashinmei, Fujisawa-shi, Kanagawa, 251-8501 Japan Abstract Rolling contact fatigue (RCF) tests were conducted on rolling bearings, with holes micro-drilled at the mid-point of the tracks. In all of the RCF tests, fatigue cracks initiated at the edge, near the base of the drilled holes, later propagating by shear-mode. Even in the un-flaked specimens tested up to N = 2×10 8 cycles, short fatigue cracks were discovered at the edges. Using the stress intensity factor (SIF) range, as calculated for the initial defect size, fatigue life data were uniformly gathered inside a narrow band, irr spective of the diameters an depths of the oles. In addition, it was deter ined that the crack-size dependency of the thr shold SIF range, well-kn wn for Mode I fatigue cracks, also exists for Mod II fatigue cracks, as produced ft r rolling contact. The values of the threshold SIF range obtained by the RCF tests were in good agreement wit those obtained in the torsional f tigue tests u der static compress on. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Com ittee of the 3rd International Symposium on Fatigue Design and Material Defects. 3 rd International Symposium on Fatigue Design and Material Defects, FDMD 2017, 19-22 September 2017, Lecco, Italy Quantitative Evaluation of the Flaking Strength of Rolling Bearings with Small Defects (Part 2: Evaluation of the Flaking Strength of Rolling Bearings with Small Drilled Holes, based on the Stress Intensity Factor) Hisao Matsunaga a,b,c , Sho Hashimoto d,e, *, Hiroki Komata e , a Kyushu Univ. Faculty of Engineering, 744 Motook , Nishi-k , Fukuoka-shi, Fukuoka, 819-0395 Japan b Kyushu Univ. International Institute for Carbon-Ne tral Energy Research (I2CNER), 744 Motooka, Nishi-ku, Fukuoka-shi, Fukuoka , 819-0395 Japan c Kyushu Univ. Research Center for Hydrogen Industrial Use and Storage (HYDROGENIUS), 744 Mot oka, Nishi-ku, Fukuoka-shi, Fukuoka, 819-0395 Japan d Kyushu Univ. Graduate School of Engineering, 744 Motook , Nishi-ku, Fukuoka-shi, Fukuok 819 0395 e Core Technology R&D Center, NSK Ltd., 1-5-50 Kugenumashinmei, Fujisawa-shi, Kanagawa, 251-8501 Japan Abstract Rolling contact fatigue (RCF) tests were conducted on rolling bearings, with holes micro-drilled at the mid-point of the tracks. I all of the RCF tests, fatigue cracks initiated at the edge, near the base of the drilled holes, later propagating by shear-mod . Even in the un-flaked specimens tested up to N = 2×10 8 cycles, short fatigue cracks were discovered at the edges. Using the stress intensity factor (SIF) range, as calculated for the initial defect size, fatigue life data were uniformly gathered inside a narrow band, irrespective of the diameters and depths of the holes. In addition, it was determined that the crack-size dependency f the threshold SIF range, well-known for Mode I fatigue cracks, also exists for Mode II fatigue cracks, as produced fter rolling contact. The values of th thresh ld SIF ra e o tained by the RCF tests were in good agreement with those obtained in the torsional fatigue tests under static compression. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of the 3rd International Symposium on Fatigue Design and Material Def cts. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Copyright © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of the 3rd International Symposium on Fatigue Design and Material Defects. Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation.

* Corresponding author. Tel.: +81-466-21-3079; fax: +81-466-27-9766. E-mail address: hashimoto-sho@nsk.com * Correspon ing author. Tel.: +81-466-21-3079; fax: +81-466-27-9766. E-mail address: hashimoto-sho@nsk.com

2452-3216 © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of the 3rd International Symposium on Fatigue Design and Material Defects. 2452 3216 © 2017 Th Authors. Published by Elsevier B.V. P er-review under responsibility of the Scientific Committee of the 3rd International Symposium on Fatigue Design and Material Defects.

* 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 PCF 2016.

2452-3216 Copyright  2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of the 3rd International Symposium on Fatigue Design and Material Defects. 10.1016/j.prostr.2017.11.113