PSI - Issue 13

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com ScienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structural Integrity 13 (2018) 1888–1894 Available online at www.sciencedirect.com ScienceDir ct 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. ECF22 - Loading and Environmental effects on Structural Integrity Crack growth analysis and residual life estimation of structural elements under mixed modes 1 Mirko Maksimović, 2 Ivana Vasović, 3 Kat rina Maksimović, 4 Stevan Maksimović, 5 Dragi Stamenković 1 Belgrade Waterworks and Severage, maksimovic.mirko@gmail.com 2 Lola Institute, Kneza Višeslava 70a, Belgrade, Serbia, ivanavvasovic@gmail.com 3 Secretariat for Utilities and Housing Services Water Management, Kraljice Marije 1, 11120 Belgrade, Serbia, kmaksimovic@mts.rs 4 Military T ch ical Institute, Ratka Resanovica 1, Belgrade, s.maksimovic@mt 5 IDS GmbH Oberhausen, Germany, dragi33@gmail.com Attention in this work is focused to crack growth analysis and residual life estimation of metal structural components under mixed modes I/II. Primary attention of this investigation is numerical simuation crack growth trajectory. For this purpose FEM is used together with the maximum tangential stress (MTS) criterion. To determine crack growth trajectoties of cracked structural compo ents under mixed modes convencional singular finite lements are used. In this investi ation specimen with wo holes and crack between its is consider d. The crack betwe n two oles is defined to achieve mixed mode I/II crack growth trajectory.The main objective of this ork is to develop a computational analysis methodology to simulate realistic crack growth and to predict remaining life and residual strength of complex aircraft and another flight structures. Modern aircraft structures are designed using damage tolerance philosophy. This design philosophy envisions sufficient strength and structural integrity of the aircraft to sustain major damage and to avoid catastrophic failure. An special attention in this work is focused to study the effects of initial angle of crack between two holes on crack gr wth traj ctories. Computatio crack growth trajectories are compared with own experimental results. There ar good agreements in determining the path of th crack growth nd life estimation. Good agreement between co putatio and experimental crack growth trajectory is obtain d. ECF22 - Loading and Environmental effects on Structural Integrity Crack growth analysis and residual life estimation of structural e e ents under mixed modes 1 Mirko Maksimović, 2 Ivana Vasović, 3 Katarina Maksimović, 4 Stevan Maksimović, 5 Dr gi Stamenković 1 Belgrade Waterworks and Severage, maksimovic.mirko@gmail.com 2 Lola Institute, Kneza Višeslava 70a, Belgrade, Serbia, ivanavvasovic@gmail.com 3 Secretariat for Utilities and Housing Services Water Management, Kraljice Marije 1, 11120 Belgrade, Serbia, kmaksimovic@mts.rs 4 Military Technical Institute, Ratka Resanovica 1, Belgrade, s.maksimovic@mts 5 IDS GmbH Oberhausen, Germany, dragi33@gmail.com bstract Att ntion in this work is focused to crack g owth analysis and residual lif estimation of metal structural components unde mixed modes I/II. Primary t tion f this investigatio is numerica imuation crack growth trajectory. For th s pur ose FEM is use together ith the maximum tangential stress (MT ) criterion. To determine crack growth trajectoties of cracked s ructural comp nents under mixed modes convencional singular finite e ements are used. In th s investig t on specimen wi h two holes and crack between its is considered. T e crack b tween two holes is de ined to a hieve mixed mode I/II c a k growth trajectory.The main objective of t s w rk is to develop a computatio al analy is methodology to simulate real s ic crack growth and predict remaining lif residual strength of omplex aircraft and nother flight tructures. Modern aircraft structures are des gned using damage tolerance p ilo ophy. This design philosophy envisions sufficient strength nd structu al integrity of t e aircr ft to sustain major damag n t avo d catas rophic fa lure. An speci l attention in this work is focused to stu y the eff cts of initial angl of rack between two holes o cra k growth trajectories. Computation crack growth trajectories are compared with own experimental results. There are good agreements in determining the path of the crack growth and life estimation. Good agreement between computation and experimental crack growth trajectory is obtained. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Keywords: Fatigue, crack growth, trajectory, residual life, mixed modes, finite elements © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. Keywords: Fatigue, crack growth, trajectory, residual life, mixed modes, finite elements Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation. Abstract

Nomenclature a Nomenclature a

crack length

N number of cycle da/dN the fatigue crack growth rate crack length

* Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt 2452-3216© 2018 The Authors. Published by Elsevier B.V. Peer-review und r responsibil ty of the ECF22 organizers. 2452-3216© 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. number of cycle da/dN the fatigue crack growth rate N

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.2018.12.324