PSI - Issue 2_A

ScienceDirect Available online at www.sciencedirect.com Av ilable online at ww.sciencedire t.com Sci ceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Struc ural Integrity 2 (2016) 1514–1521 Available online at www.sciencedirect.com Sci nceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2016) 000 – 000

www.elsevier.com/locate/procedia www.elsevier.com/locate/procedia

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. 21st European Conference on Fracture, ECF21, 20-24 June 2016, Catania, Italy Dimensional stability of coarse-grained and submicrocrystalline TiNi shape memory alloy for medical use under quasistatic and cyclic bending O.A. Kashin a *, E.F. Dudarev b , A.I. Lotkov a,b , V.N. Grishkov a a Institute of Strength Physics and Materials Science SB RAS, 2/4, pr. Akademicheskii, Tomsk 634055, Russia b National R search Tomsk State University, 36, pr. Lenin, Tomsk 634050, Russia The paper reports on a comparative study of inelastic strain accumulation in coarse-grained and submicrocrystalline titanium nickelide (TiNi) under quasistatic and cyclic loads. It is shown that the formation of submicrocrystalline structure in TiNi by equal channel angular pressing provides a steep increase in its strain resistance under quasistatic and cyclic loads. The contribution of dislocation an martensitic mechanisms t residual train accumulation u der ifferent loading conditions is analyz d. © 2016 The Authors. Published by Elsevier B.V. Peer-revi w under responsibility of the Scientific Committee of ECF21. Keywords: TiNi s ape memory alloy; quasistatic an cyclic bending; strain accumulation; di ensional stability 1. Introduction Metal and alloy implants are now widely used for treatment of diseases and injuries. One of the major characteristics of implant is their fatigu life, which determines how long an implant will properly serve in a body under cyclic loads induced by natural human motions. Implants, in most cases, are designed to function at stresses below the yield strength of materials of which th y are made. However, even at these stresses, residual inelastic strain is accumulated in implants, and the rate of its accumulation determines the dimensional stability of implants, 21st European Conference on Fracture, ECF21, 20-24 June 2016, Catania, Italy Dimensional stability of coarse-grained and submicrocrystalline TiNi shape memory alloy for medical use under quasistatic and cyclic bending O.A. Kashin a *, E.F. Dudarev b , A.I. Lotkov a,b , V.N. Grishkov a a Institute of Strength Physics and Materials Science SB RAS, 2/4, pr. Akademicheskii, Tomsk 634055, Russia b National Research Tomsk State University, 36, pr. Lenin, To sk 634050, Russia Abstract The paper reports on a comparative study of inelastic strain accumulation in coarse-grained and submicrocrystalline titanium nickelide (TiNi) under quasist tic and cyclic loads. It i shown that the formati n of submicrocry talline structure in TiNi by equal channel angular pressing provides a steep increase in its strain resistance under quasistatic and cyclic loads. The contri ution of dislocation and martensitic m ch nisms to r sidual strain accumulation under different loading conditions is analyzed. © 2016 The Authors. Publish d by Elsevier B.V. Peer-review under espons bility of the Scientific Committee of ECF21. Keywords: TiNi shape memory alloy; quasistatic and cyclic bending; strain accumulat on; dimensional stability 1. Introduction Metal and alloy implants are now widely used for treatment of diseases and injuries. One of the major charac eristics of implants is their fatigue l f , which determines how long an impl t will properly serve in a body und r cyclic loa s induced by natural human m t ons. Impla t , in most c ses, are designed to function at stresses below the yield stre gth of materials of which they are made. However, even t th e stresses, res dual inelastic strain is accumulat d in implan s, and the rat of its accumulation determines the dimensional stability of imp n s, Copyright © 2016 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/). Peer-review under responsibility of the Scientific Committee of ECF21. © 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

* Corresponding author. Tel.: +7-382-228-6920. E-mail address: okashin@ispms.tsc.ru * Corresponding author. Tel.: +7-382-228-6920. E-mail address: okashin@ispms.tsc.ru

* Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt 2452-3216 © 201 6 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. 2452-3216 © 201 6 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21.

2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Copyright © 2016 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license ( http://creativecommons.org/licenses/by-nc-nd/4.0/ ). Peer review under responsibility of the Scientific Committee of ECF21. 10.1016/j.prostr.2016.06.192