PSI - Issue 7

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com ienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 P o edi Structural Integr ty 7 (2017) 33–35 Structural Integrity Procedia 00 (2017) 000–000 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2017) 000–000 ScienceDirect

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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. Copyright © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of the 3rd International Symposium on Fatigue Design and Material Defects. 3rd International Symposium on Fatigue Design and Material Defects, FDMD 2017, 19-22 September 2017, Lecco, Italy Challenges for Gas Turbine Engine Components in Power Generation Martin Hughes* Siemens Industrial Turbomachinery Ltd., Waterside South, Lincoln, LN5 7FD, United Kingdom Abstract Some of the challenges relating to gas turbine component integrity and life are summarized. The demanding requirements for materials and components in the gas turbine operating environment has driven th huge developments in analysis methods, materials and testing over the last few decades. New technologies and also evolving operating environments relating particularly to the need for flexible operation will continue to have a significant influence on the evolution of component design and lifing methods. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of the 3rd International Symposium on Fatigue Design and Material Defects. Keywords: Gas turbine, power generation, integrity. Gas turbines can still be regarded as having a relatively recent history in the field of conventional energy generation even though the original ideas may be traced back much earlier. Early practical gas turbines appeared during the second quarter of the twentieth century. The potential for high power to weight ratio was a clear driver in aero applications. Industrial gas turbines started to find applications in the booming oil and gas industry, marine, industrial mechanical drives, and an increasing use for electrical power generation. Today’s machines typically rang in s ze from single digit to hundreds of mega Watts capacity and represent a major contributor to the electrical 3rd International Symposium on Fatigue Design and Material Defects, FDMD 2017, 19-22 September 2017, Lecco, Italy Challenges for Gas T bine Engi e Components in Power Generation Martin Hughes* Siemens Industrial Turbomachinery Ltd., Waterside South, Lincoln, LN5 7FD, United Kingdom Abstract Some of the challenges relating to gas turbine component integrity and life are summarized. The de a ding requirements for materials and components in the gas turbi e operating environment has driven t e huge developments in analysis methods, aterials and testing over the last few decades. New technologies and also evolving operating environments relating particularly to the need for flexible operation will continue to have a significant influence on the evolution of component design and lifing methods. © 2017 The Aut ors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of the 3rd International Symposium on Fatigue Design and Material D fects. Keywords: Gas turbine, power generation, integrity. Gas turbines can still be regarded as having a relatively recent history in the field of conventional energy generation even though the original ideas may be traced back much earlier. Early practical gas turbines appeared during the second quarter of the twentieth century. The potential for high power to weight ratio was a clear driver in aero applications. Industrial gas turbines started to find applications in the booming oil and gas industry, marine, industrial mechanical drives, and an increasing use for electrical power generation. Today’s machines typically range in size from single digit to hundreds of mega Watts capacity and represent a major contributor to the electrical © 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.: +44 1522 586836; fax: +44 1522 584908. E-mail address: hughes.peter@siemens.com

2452-3216 © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of the 3rd International Symposium on Fatigue Design and Material Defects. 2452-3216 © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of the 3rd International Symposium on Fatigue Design and Material Defects. * Corresponding author. Tel.: +44 1522 586836; fax: +44 1522 584908. E-mail address: hughes.peter@siemens.com

* 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 PCF 2016.

2452-3216 Copyright  2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of the 3rd International Symposium on Fatigue Design and Material Defects. 10.1016/j.prostr.2017.11.057