PSI - Issue 5

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com Sci ceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 5 (2017) 64 –646 Available online at www.sciencedirect.com ScienceDirect StructuralIntegrity Procedia 00 (2017) 000 – 000 il l li t . i i t. tr t r lI 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 Structural integrity analyses of two gas tur ines exhaust systems used for naval propulsion António Soares a , Rui F. Martins b, *, António F. Rodrigues Mateus c a Faculty of Sciences and Technology, Universidade Nova de Lisboa, Department of Mechanical and Industrial Engineering, Campus de Caparica, 2829-516 Caparica, Portugal b UNIDEMI, Faculty of Sciences and Technology, Universidade Nova de Lisboa, Department of Mechanical and Industrial Engineering, Campus de Caparica, 2829-516 Caparica, Portugal c Arsenal do Alfeite, S.A., Base Naval de Lisboa, Alfeite, 2810-001 Almada, Portugal Heating and cooling cycles, as well as accelerations and decelerations, to which naval gas turbine’s exhaust systems under study are submitted to, could lead to the nucleation and propagation of cracks, and result in the reduction of its xpected fatigue life. The paper herein presented refers to the numerical simul ons f the m chanical and t ermal behaviours of two different gas turbine’s exhaust systems used in naval propulsion. In addition, some experimental values that were collected, namely temperature and pressure, served as input values for the finite element analyses carried out. The analyses made to the exhaust systems revealed the existence of high stresses near the lower support flanges, which are mainly caused by the non-uniform thermal expansion that the exhaust systems are subjected to. Additionally, redesigned exhaust systems were studied in order to enhance the thermal behaviour of the exhaust systems and, therefore, increasing its fatigue life. The modifications introduced in the exhaust systems resulted in the reductio of the induced stresses. However, frequent surveys should be perf rmed to the critical welds of the exhaust systems, in order to prevent cr ck propagation from the weld toes. Moreover, high quality fabrication is required in order to avoid the presence of initial defects in the structure. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. , teu c a lt f i l , i i i , t t f i l I t i l i i , i , - ica, t l b I I, lt f i l , i i i , t t f i l I t i l i i , i , - i , t l c l lf it , . ., l i , lf it , - l , t l ti li l , ll l ti l ti , t i l t i t t t itt t , l l t t l ti ti , lt i t ti it e t ti li . i t t t i l i l ti t i l a t l i t i t t i t t i l l i . iti , e i t l l t t ll t , l t t , i t l t i it l t l i t. l t t t t s l t i t i t t e lower support flanges, which are mainly caused by the non-uniform thermal expansion that the exhaust system are subject t . iti ll , i t t t i i t t t l i t st t , t , i i it ti li . i i ti i tr u i n . e , o s , . , i lit i ti i i i t i t i iti l t i t t t . t . li lse i . . i unde i ilit t i ti i itt . © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017 Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation. Keywords:Structural integ ity; Design and structural assessment; exhaust systems; gas turbine; naval propulsion; AISI 316L. : t t l i t rit ; i t t l t; t t ; t i ; l l i ; I I . Abstract

* Corresponding author. Tel.: +351-21-294 85 67; fax: +351-21-294 85 31. E-mail address: rfspm@fct.unl.pt i t r. l.: - - ; f : - - . - il : rf f t. l. t rr

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.2017.07.033 * 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. l i r . . i i ilit t i ti i itt . - t r . li