PSI - Issue 2_B

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com ScienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Struc ural Integrity 2 (2016) 3752–3757 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2016) 000–000

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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 Load separation in 17 mm wide CT specimen of Zr-2.5Nb pressure tube material A. K. Bind a,b *, S. Sunil a , R. N. Singh a,b , Abhishek Tiwari b , J. K. Chakravartty a , a Bhabha Atomic Research Centre, Trombay, Mumbai-400085,India b Homi Bhabha National Institute, Anushakti Nagar, Mumbai-400094, India Abstract In PHWR community 17 mm wide curved compact tension (CCT) specimen is most commonly used for fracture toughness testing in axial direction of pressure tube. This specimen geometry is different from Conventional CT specimen (ASTM E 1820– 11) in two aspects. First being the curvature of the CCT specimen and second is that it does not meet the alternate thickness criteria of 2≤ W / B ≤4 for B = 3.6 mm. Despite these differences, the eta and gamma factors used for the fracture toughness measurement of Conventional CT specimen according to ASTM E 1820 –11 are also applied for CCT specimen. In this work, 17 mm wide blunt notched Conventional CT specimens of Zr-2.5Nb pressure tube with different a/W ratios between 0.3 and 0.7 were loaded up t m x mum l ad. The lo d s parabilty was checked and eta factor was c lculate using load separation method. Th investigation of separation parameter ( S for r ference racks ( a i /W ) b tw en 0.45 and 0.7 sh wed that (a) load was separable over whole range f plastic displacement for the CT specimens with a i /W between 0.45 and 0.7, except for small initial inseparable region, and (b) load was not separable over whole range of plastic displacement for the CT specimens with a i /W of 0.35 and 0.40. The small inseparable region in the CT specimens with a i /W between 0.45 and 0.7 is reported in literature to be due to initial blunting of the CT specimen. The eta factor, calculated using load separation method proposed by Sharobeam and Landes, was found to have a constant value of 2.08 for a i /W in range of 0.45 and 0.70. The eta factor was found to be lower than that reported by Sharobeam and Landes as well as in ASTM 1820 – 11. Since load was not separable for CT specimens with a/W of 0.35 and 0.4, eta factor derived for this CT geometry cannot be used for a/W below 0.45.

© 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. Copyright © 2016 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (http://creativ commons.org/licenses/by-nc-nd/4 0/). Peer-review under responsibility of the Scientifi Committee of ECF21.

Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation. Keywords: PHWR; curved CT; load separation; separtion parameter; eta factor

* Corresponding author. Tel.: +91-22-2559-2170; fax: +91-22-2550-5151. E-mail address: akbind@barc.gov.n

* 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.

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.2016.06.466