PSI - Issue 7

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 Structu al Integrity 7 (2017) 351–358 Available online at www.sciencedirect.com ScienceD r ct 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. 3rd International Symposium on Fatigue Design and Material Defects, FDMD 2017, 19-22 September 2017, Lecco, Italy Fatigue strength evaluation of small defect at stress concentrat on Mari Åman a *, Yuzo Tanaka b ,Yukitaka Mur kami b, c , Heikki Remes a , Gary Marquis a a Aalto University, School of Engineering, Department of Mechanical Engineering, PO Box 14300, FI-00076 Aalto, Finland b KMTL (Kobe Material Testing Laboratory Co. Ltd., Kako-gun, Hyogo, 675-0155, Japan c Department of Mechanical Engineering, Kyushu University, 744 Motooka, Nishi-ku, Fukuoka 819-0395, Japan Abstract The effect of individual large notches on the fatigue strength of components is one of the oldest and most studied topics in the history of metal fatigue. When a small defect is present at the notch root, both the stress concentration of the main notch and the effect of the small defect interact and simultaneously influence the fatigue strength. The effect of the main notch can be evaluated from the viewpoint of stress concentration and stress gradient. Both have a strong influence on the fatigue notch factor. The √ parameter model has been successfully applied to fatigue limit evaluation of materials containing small defects under uniform stress condition. If a small defect is present at the notch root, the effect of stress gradient must be also considered in the application of the model. In the present study, the fatigue tests and fatigue crack growth analyses are carried out for specimens containing a small defect with the size √ area =46.3 µ m at the root of notch with 1mm depth and root radius of 1.0mm or 0.3mm. Fatigue limit predictions are made based on the √ area parameter model and the stress intensity factor analyses for a small crack subject to a steep st ss gradient. Existing fatigue notch effect methods are reviewed and used in fatigue limit predictions for comparison. Moreover, new fatigue notch effect method based on the √ area parameter model is proposed. The greatest advantage of the proposed method is that it can pre ict fatigue limit usi g easily obtainab e parameters and without requiring fatigue tests or troublesome analyses. Suggestions for the extension of the proposed method to practical engineering problems are also made. 3rd International Symposium on Fatigue Design and Material Defects, FDMD 2017, 19-22 September 2017, Lecco, Italy Fatigue strength evaluation of small defect at stress concentration Mari Åman a *, Yuzo Tanaka b ,Yukitaka Murakami b, c , Heikki Remes a , Gary Marquis a a Aalto University, School of Engineering, Department of Mechanical Engineering, PO Box 14300, FI-00076 Aalto, Finland b KMTL (Kobe Material Testing Laboratory Co. Ltd., Kako-gun, Hyogo, 675-0155, Japan c Department of Mechanical Engineering, Kyushu University, 744 Motooka, Nishi-ku, Fukuoka 819-0395, Japan Abstract The effect of individual large notches on the fatigue strength of components is one of the oldest and most studied topics in the history of metal fat g e. Wh n a small defect is presen at the not h ro t, both the stress concentration of the ma n notch and effect of the small defect int ract and simultaneously i fluence the fatigue strength. The effect of the main notch can be ev lua ed from the vi wpoint o stress concentrat on and stre s gradi nt. Both have a tro g influence on the fatigue otch fa tor. The √ parameter model has be n successfully applied to fatigu limit evaluation f materials c taining small defects under uniform stress conditi n. If mall defe t i present at the notch root, the effect of stress gr dient must be also considered in the application of the mo el. In the present study, th fatigue t sts and fatigue crack growth analys s are carried out for specimens containing a small defect with the size √ area =46.3 µ m at the root of notch with 1mm depth and root radius of 1.0mm or 0.3 m. Fatigue limit predictions are mad based on the √ area parameter model and the stress intensity fac or analyses for a small crack subject to a st ep stress gradient. Existing fatigue notch eff ct methods are r viewed and used in fatigue limit predictions for comparis n. Moreover, new fatigue notch effect method based on the √ rea parameter mod l s proposed. The grea est advantage of the pr posed method is that it can predict fatigue limit using e sily obt inable parameters and without requiring fatigue tests or tr ubleso e analys . Suggestions for he xtens on of the proposed method to pr ctical engineer ng problems are lso made. © 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. 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.

* Corresponding author. Tel.: +358445743900 E-mail address: mari.aman@aalto.fi * Corresponding author. Tel.: +358445743900 E-mail address: mari.aman@aalto.fi

* Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt 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 The Authors. Published by Elsevier B.V. Peer review under r sponsibility of the Scientific Committee of the 3rd International Symposium on Fatigue Design and Material Defects.

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.2017.11.099