PSI - Issue 5

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com Scie ceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Struc ural Integrity 5 (2017) 1326–1333 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 ( )

www.elsevier.com/locate/procedia . l i r. /l t / r i

www.elsevier.com/locate/procedia

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 damag in spline couplings: nume ical simulations and experimental validation Francesca Curà a *, Andrea Mura a , Federica Adamo a a Politecnico di Torino, Department of Mechanical and Aerospace Engineering, C.so Duca degli Abruzzi 24, Torino 10129, Italy Spline couplings are often over dimensioned concerning fatigue life, but they are subjected to wear phenomena. For as concerns fatigue life, standard design methods consider only a part of the spline teeth to be in contact and this brings to underestimate the components life, so a better understanding about component fatigue behavior may allow to a weight reduction and a consequent increasing of machine efficiency. On the other hand, wear damage may cause spline coupling run outs; this phenomenon is generally caused by the relative sliding between engaging teeth; the sliding may be due to kinematic conditions (angular misalignment between shafts) of teeth deflection. In order to obtain component optimization, both fatigue and wear behavior have to be taken into account. Standard spline coupling design methods do not properly consider wear damage and they evaluate fatigue life with big approximations. In this work fatigue damage are experimentally and numerically investigated while wear damage has been experimentally evaluated. Experimental results have been obtained by a dedicated test rig. Fatigue tests have been performed by means of a special device connected to a standard fatigue machine. Tests have been done by varying the most important working parameters (torque and misalignment angle). Experimental results have been compared with standard design methods to evaluate if and how they may over dimension the components. Results show that concerning the fatigue life, the actual component life is higher respect to that calculated by standard methods. Regarding wear behavior, results shows that whenever a relative motion between engaging teeth is present, wear damage appears. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. Madeira, Portugal e e a r a e a a lit i i i , t t f i l i i , . li i , i , It l li li t i i i ti li , t t j t t . ti li , t i t i l t t li t t t i t t t i i t ti t t t li , tt t i t t ti i ll t i t ti t i i i i i . t t , li li t ; t i i ll t l ti li i t i t t ; t li i t i ti iti l i li t t t t t l ti . t t i t ti i ti , t ti i t t i t t. t li li i t t l i t l t ti li it i i ti . t i ti i t ll i ll i ti t il i t ll l t . i t l lt t i i t t t i . ti t t i l i t t t ti i . t i t t important workin rameters (torque and misalignment an l . i t l lt it t i methods to evaluate if and how they may over dimension t t . lt t t i t ti li , t t l t li i i t t t t l l t t t . i i , lt t t l ti ti t i t t i t, . t . li l i . . i i ilit t i ti i itt . © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017 Abstract

© 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Keywords: Spline coupling; fretting; wear; fatigue; test rig : li li ; fr tti ; r; f ti ; t t ri

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

* Corresponding author. Tel.: +39 011-0906930; fax: +39 011-0906999. E-mail address: andrea.mura@polito.it rr i t r. l.: - ; f : - .

- il

:

r . r

lit .it

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.2017.07.141 * 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 .