PSI - Issue 13

ScienceDirect Available online at www.sciencedirect.com Available online at ww.sciencedire t.com ienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 13 (2018) 631–635 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2018) 000–000 Available online at www.sciencedirect.com ScienceDirect Structural I t gri y 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 Authors. Published by Elsevier B.V. Pe r-r view und r responsibility of the ECF22 organizers. ECF22 - Loading and Environmental effects on Structural Integrity Scatter of fatigue life regarding stress concentration factor Przemysław Strzelecki a * a In stit u te of Me ch a n i c a l Eng i n eeri ng, Un i v ersit y of S c ie nc e a n d T e chnology, 85 ‐ 789 By d go s zcz, Pol a n d , PL Abstract The design process of new structural components requires to determine the fatigue life of those components at dynamic loads that change over time. To extend the fatigue life, the shape of the component must maintain the smallest possible stress concentration factor for all its surfaces. Verification calculations use the fatigue characteristics for each structural component (or determined for the material used corr cted by the fatigue notch factor) with the p obability of failure at 5% or lower. The prob bility is determined based on the analysis of risk for human life, economic losses, environmental risk etc. The study shows the effects of the shape parameter on the scatter of the test results. The tests were carried out on AW-6063 aluminium alloy, purchased as a 10 mm dia. drawn bar. The rotating bending fatigue tests were carried out on smooth and notched specimens with 1.4, 2 and 2.6 stress concentration factor. © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. Keywords: Type your keywords here, separated by semicolons ; 1. Introduction Fatigue life must be calcu ated for a new design elements. Fir tly, a medi n S-N curve for smooth specimens is estimated. Then, the median S-N curve for notched element can be derived by shifting the median S-N curve for smooth specimens to the left by divide stress amplitude by stress concentration factor or fatigue notch factor. The design S-N curve for notched element is obtained by shifting the median S-N curve for notched specimens to the left by factor depending K , which depends on the requirement probability of failure. More detail can be found in Lee et al. (2005), Strzelecki and Sempruch (2016) and ASTM E-739-91 (2006). In this procedure it is assumed that scatter of fatigue life ECF22 - Loading and Environmental effects on Structural Integrity Scatter of fatigue life regarding stress concentration factor Przemysław Strzelecki a * a In stit u te of Me ch a n i c a l Eng i n eeri ng, Un i v ersit y of S c ie nc e a n d T e chnology, 85 ‐ 789 By d go s zcz, Pol a n d , PL Abstract The design process of new structural components requires to determine the fatigue life of those components at dynamic loads that change over time. To extend the fatigue life, the shape of the component must maintain the smallest possible stress concentration factor for all its surfaces. Verification calculations use the fatigue characteristics for each structural component (or determined for the materi l used corrected by the fatigue notch factor) with the probability of failure at 5% or lower. The probability is determined based on the analysis of risk for huma lif , economic losses, environmental ri k etc. The study sh w the effects of the shape parameter on the scatter of the test results. The tests were carried out on AW-6063 aluminium alloy, purchased as a 10 mm dia. drawn bar. The rotating bending fatigue tests were carried out on smooth and notched specimens with 1.4, 2 and 2.6 stress concentration fact r. © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. Keywords: Type your keywords here, separated by semicolons ; 1. Intro uction Fatigue life must be calculated for a new design elements. Firstly, a median S-N curve for smooth specim ns is estimated. Then, the median S-N curve for notched element can be derived by shifting the median S-N curve for smooth specimens to the left by divide stress amplitude by stress concentration factor or fatigue notch factor. The design S-N curve for notched element is obtained by shifting the median S-N curve for notched specimens to the left by factor depending K , which depends on the requirement probability of failure. More detail can be found in Lee et al. (2005), Strzelecki and Sempruch (2016) and ASTM E-739-91 (2006). In this procedure it is assumed that scatter of fatigue life © 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.

* 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 organizers. * Corresponding author. Tel. +48-52-340-86-72; fax: +48-52-340-82-79. E-mail address: p.strzelecki@utp.edu.pl * Corresponding author. Tel. +48-52-340-86-72; fax: +48-52-340-82-79. E-mail ad ress: p.strzelecki@utp.edu.pl

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.2018.12.104