PSI - Issue 7

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 Structu al Integrity 7 (2017) 174–181 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. 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. 3rd International Symposium on Fatigue Design and Material Defects, FDMD 2017, 19-22 September 2017, Lecco, Italy Effect of Grain Size on Low Cycle Fatigue Life in Compressor Disc Supe lloy GH4 69 at 600 °C L.L. Liu a , D.Y. Hu a,b,c *, D. Li a , R.G. Hu d , Y.X. Gu d and R.Q. Wang a,b,c a School of Energy and Power Engineering, Beihang University, 100191 Beijing, China; b Collaborative Innovation Center of Advanced Aero-Engine, 100191 Beijing, China; c Beijing Key Laboratory of Aero-Engine Structure and Strength, 100191 Beijing, China; d Gas Turbine Establishment, Aero Engine Corporation of China, 610500 Chengdu, China Abstract Nickel-based superalloy GH4169 in Chinese series (similar to Inconel 718 in the U.S. and NC19FeNb in France) has been widely used for aero-engine discs due to its excellent fatigue, oxidation and corrosion resistance at high temperature. The effect of grain size on the low cycle fatigue (LCF) lifetime was investigated in this study. Smooth specimens cut from an actual compressor disc in a civil aero-engine were conducted to strain-controlled LCF tests at 600 °C, and results showed a significant scattering in the LCF lifetime. Then grain sizes of specimens were estimated using optical microscope (OM) and Image-Pro Plus (IPP) software. A negative correlation between the grain size and LCF lifetime was found by inducing the grain refinement strengthening theory. Afterwar s, a modified Smith-Watson-Topper (SWT) model was developed to describe the depende ce f LCF lifetime on grain size. Finally, the possi le microscopic mechanism of th grain size- pen ent LCF behavior of GH4169 sup ralloy was discussed based on fracture analy s. © 2017 The Author . Published by Elsevier B.V. Peer-review und r responsibility of the Scientific Committee of th 3rd International Symposium on F tigue D sign and Material Defects. Keywords: grain size, low cycle fatigue, lifetime prediction, fracture mechanism 3rd International Symposium on Fatigue Design and Material Defects, FDMD 2017, 19-22 September 2017, Lecco, Italy Effect of Grain Size Low Cycle Fatigue Life in Compressor Disc Superalloy GH4169 at 600 °C L.L. Liu a , D.Y. Hu a,b,c *, D. Li a , R.G. Hu d , Y.X. Gu d and R.Q. Wang a,b,c a School of Energy and Power Engineering, Beihang University, 100191 eijing, hina; b Collaborative Innovation Center of Advanced Aero-Engine, 100191 Beijing, China; c Beijing Key Laboratory of Aero-Engine Structure and Strength, 100191 Beijing, China; d Gas Turbine Establishment, Aero Engine Corporation of China, 610500 Chengdu, China Abstra t Nickel-based superalloy GH4169 in Chinese series (similar to Inconel 718 in the U. . and NC19FeNb in France) has been widely used for aero-engine discs du to its excellent fatigue, oxidati n and corro ion resistance at high temperature. The effect of grai size on the low cycle fati ue (LCF) lifetime wa inv stigated in this study. S ooth specimens cut from an actual compressor disc in a civil aer -engine were co ducted to strain-controlled LCF t sts at 600 °C, and results showed a sig ifica t scattering in the LCF lifetime. Then grain sizes of specimens were estimated using optical microscope (OM) and Image-Pro Plus (IPP) software. A negative correlation between the grain size and LCF lifetime was found by inducing the grain refinement trengthening theory. Afterwards, a modified Smith-Watson-Topper (SWT) model was developed to describe the dependence of LCF lifetime on grain size. Finally, the possible microscopic mechanism of the grain size-dependent LCF behavior of GH4169 superalloy was discussed based on fractur analysis. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of he Scientific Committee of the 3rd I ternational Symposium on Fatigue Design an Material D fects.

© 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. 1. Introduction Keywords: grain size, low cycle fatigue, lifetime prediction, fracture mechanism

1. Introduction

Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation. C mpressor disc undergoes significant centrifugal l ading and generally fails under low cycle fatigue (LCF)

Compressor disc undergoes significant centrifugal loading and generally fails under low cycle fatigue (LCF)

* Corresponding author. Tel.: +86-10-82313841 E-mail address: hdy@buaa.edu.cn (D.Y. Hu) * Corresponding author. Tel.: +86-10-82313841 E-mail address: hdy@buaa.edu.cn (D.Y. Hu)

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 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.2017.11.075