PSI - Issue 6

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Available online at www.sciencedirect.com

ScienceDirect

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com Sci ceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 6 (2017) 216–223 Structural Integrity Procedia 00 (2017) 000–000 tr t r l I t rit r i ( )

www.elsevier.com/locate/procedia . l i r. /l t / r i

www.elsevier.com/locate/procedia

XXVII International Conference “Mathematical and Computer Simulations in Mechanics of Sol ids and Structures”. Fundamentals of Static and Dynamic Fracture (MCM 2017) .

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. Copyright © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the MCM 2017 organizers. Developm nt of th applied approach to analysis of beam-columns L.M. Kagan-Rosenzweig* Saint-Petersburg State University of Architecture end Civil Engineering, Russia Abstract The known approximate formula for calculating bending moment in statically determinate elastic rod under bending and com pression is generalized to the case of a statically indeterminate one loaded with a compressive force distributed along its length. The accuracy of the proposed formula corresponds with the accuracy of engineering calculations. Presented examples show that for th statically determinate rod of co stant cross- ecti n compressed by the load amounting to 90% of a critical one the m - ment error is about 3%; if the rod is statically indeterminate it is about 6%. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the MCM 2017 organizers. Keywords: longitudinal-transverse bending, bending moment, beam-columns. 1. Introduction In beam-columns be ding moment M is often c lcul ted usi g approxim te formulas h ving n engineering de gree of accuracy. For the be m-column on two inged supports, compressed by a force P of constant direction on the end such formula is i t- t t t i it f it t i il i i , i t t The known approximate formula for calculating bending moment in statically determinate elastic rod u r nding d co - r i is generalized t t f stati ll i t r i t l ed with a compressive force distributed along its length. r f t r f r l rr it t r f i ri l l ti . r t l t t f r t t ti ll t r i t r f t t r - ti r t l ti t f riti l t - t rr r i t ; if t r i t ti ll i t r i t it i t . t r . li l i r . . Peer-review under responsibility of the MCM 2017 r i r . : l it i l-tr r i , i t, - l . . i l i t i t l l t i i t l i i i . t l t i t , t t i ti t l i

P P P

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© 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. / 1 c − / c

Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation. In this formula P c is the Euler's critical force. Here and below the superscript "zero" means computation in the ab sence of compression. c i t l ' iti l . l t i t t ti i t i . t i l

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

* 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 MCM 2017 organizers. l i r . . r-r i r r i ilit f t r i r . - t r . li

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

2452-3216 Copyright  2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the MCM 2017 organizers. 10.1016/j.prostr.2017.11.033