PSI - Issue 5

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedirect.com ienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 5 (2017) 263–27 Available online at www.sciencedirect.com 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. 2nd International Conference on Structural Integrity, ICSI 2017, 4-7 September 2017, Funchal, Madeira, Portugal Material Influence on Crenellation Effectiveness in Damage Tolerant Design Jin Lu a , Volker Ventzke a , Norbert Huber a and Nikolai Kashaev a * a Institute of Materials Research, Materials Mechanics, Helmholtz-Zentrum Geesthacht, Max-Planck-Str. 1, 21502 Geesthacht, Germany Crenellation is a novel concept to heighten the fatigue resistance of the airframe structures without increasing weight. In this work the impact of materials on the effectiveness of crenellations was investigated. Two candidate alloys for future fuselage skin: AA2139 and AA2198 were s lected for this task. Firstly the microstructure and textur of those materials were investigated. Then flat and crenellated panels made of the two alloys were tested unde service-related biaxial loading conditions. A removable  5 clip gauge was applied at the crack tip to monitor the crack closure behavior during the fatigue tests. After fatigue tests the fracture surfaces were examined to interpret the respective fatigue behavior. It was found that sharp textured AA2198 alloy, which also showed tortuous shear lip morphology, has higher fatigue resistance and larger fatigue life improvement of crenellations compared with the nearly randomly textured AA2139 alloy. The correlation between the sharp texture and tortuous shear lip morphology was discussed. The source of the additional fatigue resistance and the increased crenellation efficiency in AA2198 was also analyzed. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. Keywords: Airworthiness; damage tiolerant design; fatigue crack propagation; AA2139, AA2198; microtexture 1. Introduction Fatigue is one of the utmost important concerns in the design of airframe structures. Statistics show that about 60% of failures in aircraft components are caused by fatigue damage (Bhaumik et al., 2007). To safeguard the structural integrity of aircrafts from fatigue problems, the damage tolerance approach is usually adopted. This approach requires 2nd International Conference on Structural Integrity, ICSI 2017, 4-7 September 2017, Funchal, Madeira, Portugal Material Influence on Crenellation Effectiveness in Damage Tolerant Design Jin Lu a , Volker Ventzke a , Norbert Huber a and Nikolai Kashaev a * a Institute of Materials Research, Materials Mechanics, Helmholtz-Zentrum Geesthacht, Max-Planck-Str. 1, 21502 Geesthacht, Germany Abstract Crenell tion is a nove c cept to h ight the fatigue resistance of the airfr me structures without increasing weight. In this work the impact of materials n th effectiveness of crenellations wa investig ted. Two candidate lloys for future fuselage skin: AA2139 a d AA2198 were sel cted for this task. Fi stly the microstructure and texture of those materials were investigated. Then fl t and crenellat panels made of he two alloys were tested nder service-related biaxial loading conditions. A r movable  5 clip gauge was applied at the crack tip o monitor he cr ck closure behavior during the fatigue t sts. After fatigue tests the fracture urfaces were examined to interpret the respective fatigue beh vior. It was found that shar textur d AA2198 alloy, which lso showed tortuous shear ip morphology, has higher fatigue resistanc and larg r f tigu life improvement of crenellations c mpared with th nearly randomly textured AA2139 alloy. The correlation between the sharp texture and tortuous shear lip morphology was discussed. The source of the additional fatigue resistance and the increased crenellation efficiency in AA2198 was also analyzed. © 2017 The Autho s. Publ shed by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. Keywords: Airworthiness; damage tiolerant design; fatigue crack propagation; AA2139, AA2198; microtexture 1. Introduction Fatigue is o e of he utm st important concerns in the design of airfra e structures. Statistics show that abo t 60% of failures in aircraft components are caused by fati ue damag (Bhaumik et al., 2007). To safeguard the structural integrity of aircrafts from fatigue problems, the damage tolerance approach is usually adopted. This approach requires © 2017 The Authors. P blished by Elsevier B.V. Peer-review und responsibility of the Scientific Co mittee of ICSI 2017 © 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. Abstract

2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. 2452-3216  2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017 10.1016/j.prostr.2017.07.130 * Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt 2452 3216 © 2017 Th Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. 2452-3216 © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. * Corresponding auth r. Tel.: +49-4152-87-2536; fax: +49-4152-87-42536. E-mail address: nikolai.kashaev@hzg.de * Corresponding author. Tel.: +49-4152-87-2536; fax: +49-4152-87-42536. E-mail address: nikolai.kashaev@hzg.de