PSI - Issue 2_A

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com cienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Struc ural Integrity 2 (2016) 3143–3149 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2016) 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

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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 Effect of compression Residual Stress on Fatigue Properties of Stainless Cast Steel T. Hanaki a , Y. Hayashi b , H. Akebono a *, M. Kato a , A. Sugeta a * a Department of Mechanical Science and Engineering, Hiroshima University 1-4-1 Kagamiyama, Higashi Hiroshima, Hiroshima, 739-8527 Japan b Electric Power Development Co.,Ltd, Chigasaki, Kanagawa, 253-0041, Japan Abstract In this study, in order to clarify the fatigue properties under compressive mean stresses statement and to establish the accurate evaluation method of fatigue properties of materials with compressive residual stress at surface applied by surface treatments, tension-compression fatigue tests were carried out under various kinds of compressive mean stresses by using ASTM CA6NM stainless cast steel with two kinds of modes, the load control mode and the strain control mode, respectively. In the case of tension-compression fatigue tests under the load control mode, the higher the compressive mean stress value, the higher the fatigue limit because the setting stress level was loaded simply if the compressive mean stress value beyond the compressive yield limit. In the case of tension-compression fatigue tests under the strain control mode, specimens yielded greatly at the first cycle of the fatigue tests, then the mean stress didn’t change to the tensile side with increasing the loading cycles and continued to load at the same stress level. As the results, the fatigue life decreased remarkably and specimens fractured early in comparison with a case of fatigue tests under the load control mod because shakedown beh vior was occurred. © 2016 The Authors. Published by Els vier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. a b o a a ge a a t t f i l i i i , i i i it - - i , i i i i , i i , - b l t i er Development Co.,Ltd, Chigasaki, Kanagawa, - , pan t i t , i t l i t ti ti i t t t t t t li t t l ti t ti ti t i l it i i l t t li t t t , t i i ti t t i t i i i t i t i l t t l it t i , t l t l t t i t l , ti l . t t i i ti t t t l t l , t igher the compressive mean stress value, the i t ti li it se the setting stress level was loaded simply if the compressive mean stress value beyond the compressive yield limit. t tension- i n fatigue tests under the t i t l , i i l tl t the irst c l t ti t t , t t t i t t t t il i it i i t l i l ti t l t t t l l. t lt , t ti li l i t l i i it ti t t t l t l a i . t . li l i . . i i ilit t i ti i itt . 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. Keywo ds: fatigue properties; compressive residual stress; shakedown behavior : f ti r rti ; r i r i l tr ; i r

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

* Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt 2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. l i r . . i i ilit t i ti i itt . * Corresponding author. Tel.: +81-082-424-7539 E-mail address: akebono@hiroshima-u.ac.jp, asugeta@hiroshima-u.ac.jp i t r. l.: - - - - il : ir i - . .j , t ir i - . .j - t r . li rr

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.2016.06.392