PSI - Issue 5

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com ScienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 5 (2017) 438–445 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 The study of the fatigue crack propagation in mixed mo e crack growth A. Vshivkov, A. Iziumova, O. Plekhov* Institute of Continuous Media Mechanics UB RAS, 614014 Perm, Russia This work is devoted to analysis of thermodynamics properties of the fatigue cracks propagation in metals. A theoretical description of the elastoplastic condition at the fatigue crack tip is proposed on the base of an elastic solution and a secant elastic modulus. An experimental confirmation of the theoretical approach to the heat flux calculation at the fatigue crack tip is carried out. The haracter of heat dissipation at different stages of crack propagation is studied. The investigation of the fatigue crack propagation was carried out on flat samples with stress concentrator made from stainless steel AISE 304. The stress concentrator was the side notch. Infrared thermography method and the contact heat flux sensor based on the Seebeck effect are used to monitor the dissipated thermal energy. The stress intensity factor was constant during the loading. The plastic zone shape under onotonic uniaxial loading was calculated theoretically. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. Keywords: Fatigue crack, mixed mode loading, dissipated energy, the plastic zone shape. rtugal I tit t f ti i i , , si i i t t l i t i ti t ti ti i t l . t ti l i ti t l t l ti iti t t ti ti i t l ti l ti t l ti l . i t l i ti t t ti l t t t l l l ti t t ti ti i i t. t t i i ti t i t t ti i t i . i ti ti t ti ti i t l t l it t t t t i l t l . t t t t i t . t t t t t t l t t t it t i i t t l . t i t it t t t i t l i . l ti t i i i l l i l l t t ti ll . t . lished by El e i . . i i ilit of the Scie ti i mitt f SI 2017. : ti r , i l i , i i t r , t l ti . © 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. It is well k own that real metals hav a complex structure, which is a hierarchy of different scale levels. Under deformation, the structural evolution is observed at all scale levels and leads to irreversible deformation and failure that is accompanied by energy accumulation and dissipation. Investigation of thermodynamics of deformation and t i ll t t l t l l t , i i i i t l l l . ti , t t t l l ti i t ll l l l l t i i l ti il t t i i l ti i i ti . ti ti t i ti Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation. Abstract 1. Introduction . i

* Corresponding author. Tel.: +73422378312; fax: +73422378487. E-mail address: vshivkov.a@icmm.ru i t r. l.: ; f : . - il : i . i .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.2017.07.193 * 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