PSI - Issue 13

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at www.sciencedire t.com Sci ceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structural Integrity 13 (2018) 1396–14 1 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2018) 000–000 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2018) 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. © 2018 The Auth rs. Published by Els vier B.V. Peer-review under responsibility of the ECF22 or anizers. ECF22 - Loading and Environmental effects on Structural Integrity Crack growth in titanium alloy under ultrasonic loading Valentin Tkachenko a , Alexander Nikitin b, *, Ilia Nikitin b a Moscow Aviation Institute - National Research University, Moscow, 125993, Russia b Institute for Computer Aided Design Russian Academy of Sciencies, Moscow, 123056, Russia Abstract The ultrasonic loading is usually associated with a very high cycle fatigue problem of crack initiation. It has been shown many times by Shanyavskiy (2014), Nicholas (1999) and others that such high frequency loading may to cause’unexpected’ in-service fatigue failures of turbo-jet elements, such as compressor disks and blades. Many different studies were carried out on the probl m of crack initiation in different structural materials, Bathias and Paris (2004), Mayer (2013), even for titanium alloys McEvily et al. (2008), Nikitin et al. (2016). Nonetheless the problem of early fatigue crack growth under ultrasonic loading reminded outside of main scientific interests. In the resent years the interest to this subject is increasing Perez-Mora et al. (2015), Stanzl-Tschegg et al. (2016). This paper is focused on the problem of early crack growth in two-phases titanium alloy under ultrasonic loading. The first results of crack growth tests on VT3-1 (close to Ti-6Al-4V) titanium alloy and mathematical model for prediction of crack front evolution are presented. The results of mathematical modeling are comparing with a shape of fatigue crack at the fracture pattern for curvilinear crack front. © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. Keywords: Ultrasonic loading, crack growth, mathematical modeling, crack shape prediction, kinematic diagram, titanium alloy 1. Introduction In the resent years the interest to the near threshold and early crack growth under the ultrasonic loading is growing up as mentioned by Stanzl-Tschegg (2016). Such study can be useful for prediction a critical state for engineering constructions. As reported in papers of Shanyavskiy (2014), Nicholas (1999) and others the high frequency loading may to cause the unexpected in service fatigue failures. This is because such loading regimes are ECF22 - Loading and Environmental effects on Structural Integrity Crack growth in titanium alloy under ultrasonic loading Valentin Tkachenko a , Alexander Nikitin b, *, Ilia Nikitin b a Moscow Aviation Institute - National Research University, Moscow, 125993, Russia b Institute for Computer Aided Design Russian Academy of Sc encies, Moscow, 123056, Russia Abstract The ultrasonic loading is usually associated with a very high cycle fatigue problem of crack initiation. It has been shown many times by Shanyavskiy (2014), Nicholas (1999) and others that such high frequency loading may to cause’unexp cted’ in-service fatigue failures of turbo-jet elements, such as compressor disks and blades. Many different studies were carried out on th problem of crack initiation in different structural at rials, Bathi s and Paris (2004), Mayer (2013), even for titanium alloys McEvily et al. (2008), Nikitin et al. (2016). Nonetheless the problem of early f tigu crack growth under ultraso ic lo ding reminded outside of main scientific interests. In the resent years the interest to this subject is increasing Perez-Mor et al. (2015), Stanzl-Tschegg t al. (2016). This paper is focus d on the problem of arly crack growth i two-phas s titanium alloy under ultrasonic loading. The first result of crack growth tests on VT3-1 (cl s to Ti-6Al-4V) titanium alloy and m the atical mo l for predi ti n of crack front evolution are presented. The results of mathematical modeling are comparing with a shape of fatigue crack at the fracture patter for c rvilinear crack front. © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. Keywords: Ultrasonic loading, crack growth, mathematical modeling, crack shape prediction, kinematic diagram, titanium alloy 1. Introduction In the resent years the interest to the near threshold and early crack growth under the ultrasonic loading is growing up as mentioned by Stanzl-Tschegg (2016). Such study can be useful for prediction a critical state for engineering constructions. As reported in papers of Shanyavskiy (2014), Nicholas (1999) and others the high frequency loading may to cause the unexpected in service fatigue failures. This is because such loading regimes are © 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.

* Alexander Nikitin. Tel.: +79654365980. E-mail address: nikitin_alex@bk.ru * Alexander Nikitin. Tel.: +79654365980. E-mail address: ikitin_alex@bk.ru

* Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt 2452-3216 © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. 2452-3216 © 2018 The Authors. Published by Elsevier B.V. Peer review under r sponsibility of the ECF22 o ganizers.

2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016.

2452-3216  2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. 10.1016/j.prostr.2018.12.291