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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. 21st European Conference on Fracture, ECF21, 20-24 June 2016, Catania, Italy Delamination Propagation and Load Ratio E ff ects in DCB MD Woven Composite Specimens Ido Simon ∗ , Leslie Banks-Sills, Victor Fourman, Rami Eliasi The Dreszer Fracture Mechanics Laboratory , School of Mechanical Engineering, Tel Aviv University, 69978 Ramat Aviv, Israel Abstract Double cantilever beam (DCB) specimens fabricated from 15 plies of a plain woven prepreg (G0814 / 913) arranged in a multi directional (MD) layup were tested by means of constant amplitude fatigue cycles under displacement control. Four di ff erent displacement cyclic ratios were used, namely 0.1, 0.33, 0.5 and 0.75. The delamination propagation rate da / dN was calculated from the experimental data and plotted with respect to di ff erent functions of the mode I energy release rate G I . When one of those functions, denoted here as ∆ K I was used, all of the data obtained for the di ff erent displacement ratios collapsed into one master curve. c � 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committ ee of ECF21. Keywords: Carbon fibres; Laminate; Textile composites; Delamination; Fatigue; 1. Introduction One of th most common failure modes in laminates is delamina tion or separat o of plies (Raju , 2008; Bolotin , 1996). Thus, for design purposes, damage toleranc and total life predictions, it is important to investigate the delamination resistance of composites and their behavior under both quasi-static and cyclic fatigue loads. Several studies have been carried out recently regarding delamination propagation resulting from opening mode (mode I) fatigue deformation. Nevertheless, most of the studies examined unidirectional (UD) composite materials. Moreover, currently there is no standardized protocol for testing the propagation of a delamination under fatigue loads. The only existing standard test method considering mode I deformation under fatigue loads is ASTM D6115-97 (ASTM D6115 , 2011). This standard describes a test method for mode I fati gue delamination onset of UD fiber-reinforced polymer matrix composites which leads to a ”no growth” design law. Recently, work has been carried out to specify a new standardized test method for measuring the delamination propagation rate under mode I fatigue deformation in UD comp osites (Brunner et al. , 2009; Stelzer et al. , 2014). The ability to reliably predict the delamination propagation rate may be used in order to design structures more e ffi ciently according to a damage tolerance approach. However, the exponents of the power law used to relate the propagation rate 21st European Conference on Fracture, ECF21, 20-24 June 2016, Catania, Italy Delamination Propagation and Load Ratio E ff ects in DCB MD Woven Composite Specimens Ido Simon ∗ , Leslie Banks-Sills, Victor Fourman, Rami Eliasi The Dreszer Fracture Mechanics Laboratory , School of Mechanical Engineering, Tel Aviv University, 69978 Ramat Aviv, Israel Abstract Double cantilever beam (DCB) specimens fabricated from 15 plies of a plain woven pr preg (G0814 / 913) arranged in a multi irectional (MD) layup wer tested by ans of constant amplitude fatigu cycles u de displacement control. Four di ff erent displac ment cyclic ratios were used, namely 0.1, 0.33, 0.5 and 0.75. The dela ination p opagation da / dN was calculated from the experimental d ta and plotted with respect to di ff erent functions of the mo e I en rgy release rate G I . When one of those f nctions, denoted here as ∆ K I was used, all of the data obtained for the di ff erent displacement ratios collapsed into one master curve. c � 2016 The Authors. Published by Elsevier B.V. Peer-review under r sponsibility of the Scientific Committ ee of ECF21. Keywords: Carbon fibres; Laminate; Textile composites; Delamination; Fatigue; 1. Introduction On of the m st common failure modes in laminat s is delamina i n or separation of plies (Raju , 2008; Bolotin , 1996). Thus, for design purposes, damage tolerance and total life predictions, it is import nt to investigate the delamination resistance of composites and their behavior under both quasi-static and cyclic fatigue l ads. Sev ral studies have been carried out recently regarding delamination propagation resulting from opening mode (mode I) fatigue deformation. Neverthel ss, most of the studies examined unidirection l (UD) composite materials. Moreover, curre tly here is no standardized protocol f r testing the propagation of a del mination under fatigue loads. The only existing standard test m thod considering mode I deformation under fatigue loads is ASTM D6115-97 (ASTM D6115 , 2011). This standard describes a test method for mode I fati gue delamination onset of UD fiber-reinforced polymer matrix composites which leads to a ”no growth” design law. Recently, work has been carried out to specify a new standardized test method for measuring the delamination propagation rate under mode I fatigue deformation in UD co p osites (Brunner et al. , 2009; Stelzer et al. , 2014). The bility to reliably predict the d l mination propagation rate may be used in order to design structures more e ffi ciently according to a damage tolerance approach. However, the exponents of the power law used to relate the propagation rate 21st uropean onference on Fracture, F21, 20-24 June 2016, atania, Italy l i ti r ti ti ts i sit i s Ido i on ∗ , eslie anks- ills, ictor our an, a i liasi The Dreszer Fracture Mechanics Laboratory , School of Mechanical Engineering, Tel Aviv University, 69978 Ramat Aviv, Israel Abstract Double cantilever beam (DCB) specimens fabricated from 15 plies of a plain woven prepreg (G0814 / 913) arranged in a multi directional (MD) layup wer tested by m ans of constant amplitude fatigue cycles under displacement control. Four di ff erent displacement cyclic ratios were used, namely 0.1, 0.33, 0.5 and 0.75. The delamination propagation rate da / dN was calculated from the experimental data and plotted with respect to di ff erent functions of the mode I energy release rate G I . When one of those functions, denoted here as ∆ K I was used, all of the data obtained for the di ff erent displacement ratios collapsed into one master curve. c 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committ ee of ECF21. Keywords: Carbon fibres; Laminate; Textile composites; Delamination; Fatigue; 1. Introduction ne of the ost co on failure odes in la inates is dela ina tion or separation of plies (Raju , 2008; Bolotin , 1996). Thus, for design purposes, da age tolerance and total life predictions, it is i portant to investigate the dela ination resistance of co posites and their behavior under both quasi-static and cyclic fatigue loads. Several studies have been carried out recently regarding dela ination propagation resulting fro opening ode ( ode I) fatigue defor ation. evertheless, ost of the studies exa ined unidirectional ( ) co posite aterials. oreover, currently there is no standardized protocol for testing the propagation of a dela ination under fatigue loads. The only existing standard test ethod considering ode I defor ation under fatigue loads is ST 6115-97 ( ST 6115 , 2011). This standard describes a test ethod for ode I fati gue dela ination onset of fiber-reinforced poly er matrix co posites hich leads to a ”no gro th” design la . Recently, ork has been carried out to specify a ne standardized test ethod for easuring the dela ination propagation rate under ode I fatigue defor ation in co p osites (Brunner et al. , 2009; Stelzer et al. , 2014). The ability to reliably predict the dela ination propagation rate ay be used in order to design structures ore e ciently according to a da age tolerance approach. o ever, the exponents of the po er la used to relate the propagation rate 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/). er-review under responsibility of the Scientific C mmittee 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.

* Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt ∗ Corresponding author. Tel.: + 972-3-640-8992 ; fax: + 972-3-640-7617. E-mail address: idosimon@gmail.com ∗ Corresponding author. Tel.: + 972-3-640-8992 ; fax: + 972-3-640-7617. E-mail address: idosimon gmail.com

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.2016.06.027 2452-3216 c � 2016 The Author . Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committ ee of ECF21. ∗ Corresponding author. Tel.: + 972-3-640-8992 ; fax: + 972-3-640-7617. E-mail address: idosimon@gmail.com 2452-3216 c � 2016 The Authors. Published by Elsevier B.V. e r-review under responsibility of the Scientific Committ ee of ECF21. 2452-3216 c � 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committ ee of ECF21.