PSI - Issue 13

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at www.sciencedire t.com cienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structural Integrity 13 (2018) 1093–1 98 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2018) 000–000 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2018) 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. © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. ECF22 - Loading and Environmental Effects on Structural Integrity Fatigue life analysis of edge-notches with damage Slobodanka Boljanovi ć a *, Stevan Maksimović , Andrea Carpinteri c a Mathematical Institute of the Serbian Academy of Sciences and Arts, Kneza Mihaila 36, Belgrade 11000, Serbia b VTI - Aeronautical Department, Ratka Resanovića 1, Belgrade 11000, Serbia c University of Parma, Department of Engineering and Architecture, Parco Area delle Scienze 181/A, Parma 43124, Italy Abstract In the present paper, the fracture mechanics-based computational model is proposed for estimating the strength of double-edge notched configuration under cyclic loading. The propagation of a quarter-elliptical corner crack located at one of two semi circular edge-notches is analytically investigated by means of the fatigue life to failure and crack path. Also, through experimental observations available in the literature the reliability of obtained theoretical results is discussed. © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. Keywords: Fatigue strength; quarter-elliptical corn r crack; two edge- otches; crack path. 1. Introduction The stress-concentration phenomenon that appears at critical zones where geometrical discontinuities exist may endanger the service performance of m chanical systems, due to the formation of it er he through or p rt-through (quarter- lliptical and semi-elliptical) crack-like damages. Therefore, to prevent such a harmful effect caus d by the abrupt disturbance of the stress field, the fatigue behaviour of damaged notches (holes, cutouts, grooves) should be analyzed employing the fracture mechanics-based computational models. Under cyclic loading, the failure of open and pin loaded holes with quarter-elliptical corner cracks or semi elliptical cracks has been theoretically examined by Grandt et al . (1982) using the Paris’ crack growth concept and ECF22 - Loading and Environmental Effects on Structural Integrity Fatigue life analysis of edge-notches with damage Slobodanka Boljanovi ć a *, Stevan Maksimović b , Andrea Carpinteri c a Mathematical Institute of the Serbi n Ac de y of Sciences d Arts, Kn za Mihaila 36 B lgr de 11000, Serbi b VTI - Aero autical D partme t, Ratka Resanovića 1, B lgrade 11000, Serbia c University of Parma, Department of Engineering and Architecture, Parco Area delle Scienze 181/A, Parma 43124, Italy Abstract In the present paper, the fracture mechanics-bas d c mputational model is pro osed f r estimating the strength of double- dge not hed configuration under c clic loading. The propagation of a quarter-elliptical corner crack located at one of two semi circular edge-notches is analytically investigated by means of the fatigue lif to fail re and crack path. Also, through experimental observations available in the literature the reliability of obtained theoretical results is discussed. © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. Keywords: Fa igue strength; q arter-elliptical corner crack; two edge-no che ; crack path. 1. Introduction The stress-concentration phenomenon that appears at critical zones where geometrical discontinuities exist may endanger the service performance f mechanical systems, due to the form tion of eith r the through or part-thro g (quart r-elliptical and semi-e liptical) crack-like damages. Th refore, to prevent such a harmful effect caused by the abrupt disturbance of the stress field, the fatigue behaviour of da aged notches (holes, cutouts, grooves) should be analyzed employing the fracture mechanics-based computational models. Under cyclic loading, the failure of open and pin loaded holes with quarter-elliptical corner cracks or semi elliptical cracks has been theoretically examined by Grandt et al . (1982) using the Paris’ crack growth concept and © 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 2452 3216 © 2018 Th Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. 2452-3216 © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. * Correspon ing author. Tel.:+381-63-805-6085; fax:+381-11-351-1282. E-mail address: slobodanka.boljanovic@gmail.com * Corresponding author. Tel.:+381-63-805-6085; fax:+381-11-351-1282. E-mail address: slobodanka.boljanovic@gmail.com

2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016.

2452-3216  2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. 10.1016/j.prostr.2018.12.230