PSI - Issue 5

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 Structu al Integrity 5 (2017) 422–429 Available online at www.sciencedirect.com ScienceDirect Structural Int grity 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 High cycle fatigue properties of explosively welded laminate AA2519/AA1050/Ti6Al4V Lucjan Sniezek a , Ireneusz Szachogluchowicz a , Marcin Wachowski a* , Janusz Torzewski a , Janusz Mierzynski a , a Faculty of Mechanical Engineering, Military University of Technology, 2 Gen. S Kaliskiego str., Warsaw, 00-908, Poland Abstract The paper presents preliminary results of high cycle fatigue properties, including fatigue cracking of layered laminate AA2519/AA1050/Ti6Al4V. The test material was obtained by the method of explosive bonding in direct configuration AA2519/Ti6Al4V with the intermediate layer using a AA1050 alloy. The study tested influence of the applied heat treatment on the mechanical properties of the laminate. Load applied during the tests was oscillating sinusoidal with the stress ratio R=0.1 and constant load frequency equal to 20 Hz. The tests were performed at five levels of stress amplitude dependent on shape of samples. Assumed as the criterion for the end was the number of cycles at specimen failure or when number of cycles was equal to 5 million repeats. The results indicated the beneficial effect of the applied heat treatment. The results showed an increase the fatigue of the heat-treated samples, both notched and sm oth samples. The results of electron icroscopy studies of surfac fatigue fracture allowed to d termine the location of sources of f tigue cr cking, which in the ca e of samples wit out heat treatment were in the area of border merger Ti6Al4V/AA1050. Sourc s of crack g in the elements after the heat tre ment w re located within the edge of the samples. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. 2nd International Conference on Structural Integrity, ICSI 2017, 4-7 September 2017, Funchal, Madeira, Portugal High cycle atigue p operties of explosively welded laminate AA2519/AA1050/Ti6Al4V Lucjan Sniezek a , Ireneusz Sz chogluchowicz a , Marcin Wachowski a* , Janusz Torzewski a , Janusz Mierzynski a , a Faculty of Mechanical Engineering, Military University of Technology, 2 Gen. S Kaliskiego str., Warsaw, 00-908, Poland Abstract The paper presents preliminary results of h gh cycle f tigue prop rti s, including fatigue cracking of layered laminate AA1050/Ti6Al4V. The test material wa obt ined by the method of explosiv bo ding in direct configuration AA2519/Ti6Al4V with the intermediate lay r using a AA1050 a loy. The study t sted influence of the applied heat r atm nt on the mech ical properties o the laminate. Load applied during th t sts was oscillat ng sinusoidal with the stress ratio R=0.1 and constant load frequency equal to 20 Hz. The t sts were perfor ed at five evels of stress amplitude dependent on shape of amples. Assumed as the crit rion for th end was the number of cycles at specimen failur or when number of cycles was equal to 5 million r peats. The results indicat d the beneficial effe t of the applied heat tr atment. The results sh wed an in rea e th fatigue of the heat-treated samples, b th notched and smooth samples. The results of electron mi oscopy studies of surface fatigue fr cture allowed to determin the loca io of sources of fatigue cra king, which in t e case of samples without heat reatment were n the area of border merger Ti6Al4V/AA1050. Sou ces of cracking in the el ments after e heat treat nt were located within the edge of th sampl s. © 2017 The Autho s. Publ shed by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Keywords: explosive welding, composite laminates, Al/Ti composites, highcycle fatigue ; Keywords: explosive welding, composite laminates, Al/Ti composites, highcycle fatigue ;

Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation.

* Corresponding author. Tel.:+48 261 839 245. E-mail address: marcin.wachowski@wat.edu.pl * Corresponding author Tel.:+48 261 839 245. E-mail address: marcin.wachowski@wat.edu.pl

2452-3216 © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. 2452 3216 © 2017 Th Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017.

* 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  2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017 10.1016/j.prostr.2017.07.191