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 Struc ural Integrity 5 (2017) 1342–1348 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2017) 000 – 000 il l li t . i i t. tr t r l I t rit r i ( )

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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 Fatigue behaviour of tailored blank thermoplastic composites with internal ply-drops Petr Homola a , Martin Kadlec a, *, Roman Růžek a , Jakub Šedek a a VZLU - Aerospace Research and Test Establishment, Beranovych 130, 199 05 Prague, Czech Republic. The technology of tailored blanks is used for thickness variation within a laminate plate to reduce weight in areas with lower loading. Ply-drops are used for the thickness variation and their effect on fatigue characteristics has not yet been investigated for the thermoplastic matrix. This paper describes experimental investigation of asymmetrically tapered carbon fibre-reinforced thermoplastic specimens cyclically loaded in tension. The specimens were manufactured according to design features of a rib demonstrator used in an aerospace structure. Two alternatives of transitions were investigated: single taper from 16 to 11 layers and double taper from 16 to 13 and then from 13 to 11 layers. The two taper alternative significantly improved the fatigue life. Furthermore, the effect f specimen edge quality (abrasive waterjet cutting and milling) c used the cha ge of fatigue life by 25%. In case of the run-out specimens with more than 3 million cycles, an early failure occurred at higher load levels due to damage accumulation. Fractographic examination using scanning electron icroscopy confirmed occurrence of various features typical for two observed failure modes. It was shown that laminate edges of ply-drop integrated structures should be machined precisely in order to maintain their durability. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. Keywords: Polymer composite; tailored blank; ply drop; thermoplastic; fatigue; aerospace M internal ply-drops , a - t t li t, , , li . t The t l t il l i t i i ti it i l i t l t t i t i it l l i . l t t i i ti t i t ti t i ti t t i ti t t t l ti t i . i i i t l i ti ti t i ll t i i t l ti i li ll l i t i . i t i t i t i t t i t t . lt ti t iti i ti t : i l t t l l t t t t l . t t lt ti i i i tl i t ti li . t , t t o i lit i t j t tti illi a t ti li . t t i it t illi l , l il t i l l l t l ti . t i i ti i i l t i i i t t i l t il . t t t l i t l i t t t t should be machined precisely in t intain th i ilit . t . li Elsevier B. . Peer-review under responsibility of the Scientific Committee of ICSI 2017. : l r it ; t il r l ; l r ; t r l ti ; f ti ; r © 2017 The Authors. Published by Elsevi r B.V. Peer-review under responsibility f the Scien ific Comm ttee of ICSI 2017 Abstract

© 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.: +420 225 115 409. E-mail address: kadlec@vzlu.cz rr i t r. l.: .

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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.2017.07.144 * Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt 2452-3216 © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. - t r . li l i r . . i i ilit t i ti i itt .