PSI - Issue 5

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com ienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 5 (2017) 577–583 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2017) 000 – 000 il l li t . i i t. tr t r l I t rit 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. 2nd International Conference on Structural Integrity, ICSI 2017, 4-7 September 2017, Funchal, Madeira, Portugal Method of assessment of mechanical characteristics of quasi isotropic composite laminates using experimental data from fiber- optic strain sensors Mikhail Tashkinov a *, Valeriy Matveenko а а Perm National Research Polytechnic University, Komsomolsky Ave., 29, Perm, 614990, Russia The problem of analysis and prognosis of mechanical behavior of advanced composite materials and structures during their design, manufacturing and exploitation is urgent and attracts attention of many researchers. One of the most promising areas in the field of monito ing of the state of composite structures in the process of their exploitation is connected with creation of smart materials and smart systems based on the sensor elements. The real-time data about the structure state under the subsequent analysis can be used both for mon toring the mechanical state of the structures and for refining the mathem tical models for the fracture pr cesses pr diction. T e purpose of this work is to develop a combined c mputational and experimental methodology for estimating th mechanical characteristics of structures made of polymer composite aterials (PCM). The computational component of the technique provides numerical simulation of mechanical behavior during quasistatic deformation of structures made of PCM. The experimental component is based on the measurement of deformations by fiber-optical strain sensors with Bragg gratings (FBG sensors) embedded in PCM. To refine the model parameters in accordance with the information received from the FBGs an algorithm is proposed, according to which the inverse problems are solved in order to ensure that the numerical and experimental results coincide with the specified accuracy. The implementation of the algorithm is demonstrated on the numerical example. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. a t а а ti l l t i i it , l ., , , , i stract l l i i i l i it t i l t t i t i i , t i l it ti i t tt t tt ti . t t i i i t i l it i t t t it t t i t t i l it ti i t it ti t t i l t t t l t . l ti t t t t t t t t t l i t t i t i l t t t t t i i t t t l l t t i ti . t i i t l i t ti l i t l t l ti ti t i l t i ti t t l it t i l . t ti l t t t i i i l i l ti i l i i i t ti ti t t . i t l t i t t ti i ti l t i it ti i . i t l t i it t i ti i t l it i , i t i t i l ms are solved in order to ensure that the numerical a i t l lt i i it t i i . i l t ti t l it i t t t i l l . © t . blished by Elsevier B.V. Peer-review under respo i ilit of the Scientific Committee . © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Keywords: mechanical characteristics, monitoring systems, fiber-optic strain sensors, optimization algorithm, finite element method. Keywords: mechanical characteristics, monitoring systems, fiber-optic strain sensors, optimization algorit , fi it l t t . Abstract

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

* Corresponding author. E-mail address: m.tashkinov@pstu.ru i t r. - il : .t i t .r rr

2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. 2452-3216  2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017 10.1016/j.prostr.2017.07.017 * Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt 2452-3216 © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. l i r . . i i ilit t i ti i itt . - t r . li