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 Struc ural Integrity 5 (2017) 1253–1259 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 Displacement measurement and shape acquisition of an RC helicopter blade using Digital Image Correlation Pedro J. Sousa a, *, Francisco Barros a , Paulo J. Tavares a , Pedro M. G. P. Moreira a a INEGI, Universidade do Porto, Rua Dr. Roberto Frias, 400, Porto 4200-465, Portugal The present work addresses the development and implementation of an image sensing methodology for Structural Integrity Monitoring of rot ting parts such as aircraft rotor blades. The availability of blade eformation data can enhance the quality of the numerical models and increase the confidence on the simulations. The proposed approach to the problem of deformation measurement on moving subjects uses simultaneously triggered high-speed cameras to bring the rotating subject to an apparent still position, and using 3D Digital Image Correlation (DIC) thereafter to acquire shape and measure total deformation and local strain and stress. The presented contribution involves the use of 3D DIC for displacement measurement and shape acquisition of a radio- controlled helicopter’s rotor blade under dynamic loads resultant from rotation at its minimum and maximum speeds (approximately 600 and 1200 rpm respectively). © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. Keywords: Dynamic loading; Digital Image Correlation; Structural Monitoring; Structural Integrity 1. Introduction Rotating structures appear in a wide range of areas, from cars and airplanes to energy production turbines and vacuum cleaners, making them a very important study subject [1]. Among these, the current work focuses on rotor blades that, being long flexible slender structures, undergo large deflections and torsion. When comparing the velocity distributions obtained for Contra-Rotating Open Rotor (CROR) or other Ultra High Bypass Ratio (UHBR) propulsion systems using particle image velocimetry (PIV) and computer fluid dynamics M Pedro J. Sousa , ro a a a a I I, i i t , . t i , , t - , t l t t l t i l t ti i i t l t t l t it it i t ti t i t t l . il ilit l d ti t t lit t i l l i t i t i l ti . t t l ti t i j t i lt l t i i t i t t ti j t t t till iti , i i it l l ti t t t i t t l ti l l t i t . t t i ti i l t i l t t i iti i t ll li t t l i l lt t t ti t it i i i i t l ti l . t . li l i . . Pee i i ilit t i ti i itt . Keywords: Dynamic loading; Digital Imag rr l ti ; tr t r l Monitoring; Structural Integrit . i t ti t t i i , i l t ti t i l , i t i t t t j t . t , t t t l t t, i l l i l l t t , l l ti t i . i t l it i t i ti t i t t ti Rotor (CROR) or other Ultra High ti l i t i ti l i l i t t l i i © 2017 The Authors. Published by Els vier 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: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation. Abstract

* Corresponding author. Tel.: +351-22-9578710. E-mail address: psousa@inegi.up.pt i t r. l.: - - . - il : i i. . t 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.2017.07.097 * 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