PSI - Issue 13

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at www.sciencedire t.com ScienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 13 (2018) 9 2–9 7 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2018) 000 – 000 Available online at www.sciencedirect.com ScienceDirect Structural I tegrity Procedia 00 (2018) 000 – 000

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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. ECF22 - Loading and Environmental effects on Structural Integrity Nonlinear fracture resistance parameters for cracked aircraft GTE compressor disk R.R. Yarullin*, A.P. Zakharov, I.S. Ishtyriakov Kazan Scientific Center of Russian Academy of Sciences, Kazan, Russia This study is concerned with numerical analysis of cracked aircraft gas turbine engine (GTE) compressor disk based on plastic stress intensity factor (SIF) approach. Damage accumulation and growth at operation have occurred in slot fillet of disk and blade attachment. In all of these failures, crack propa ation started fr m part-trough quarter elliptic l corner surface flows. In order to determine elastic-plastic fracture resistance parameters full-size stress-strain state analysis of compressor disk was performed for a quarter elliptical surface cracks under operation loading conditions. The process of numerical calculations includes the analysis of the elastic constraint parameters in the form of the non-singular T -stress and T Z – factor, as well as the elastic-plastic constraint parameters in the form of the local stress triaxiality h and I n -factors for the various crack sizes and different operation temperatures. The plastic SIF K p , which is shown to be sensitive to the constraint effects and environmental conditions, offers an attractive option as a self-dependent, unified parameter for use in characterizing the fracture resistance for a variety of aircraft GTE rotating components. © 2018 The Authors. Published by Elsevier B.V. Peer-review und r responsibility of the ECF22 organizers. Keywords: G s turbine engine; compress r disk; surf ce crack; plastic stress intensity factor. © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. ECF22 - Loading and Environmental effects on Structural Integrity Nonlinear fracture resistance parameters for cracked aircraft GTE compressor disk R.R. Yarullin*, A.P. Zakharov, I.S. Ishtyriakov Kazan Scientific Center of Russian Academy of Sciences, Kazan, Russia Abstract This study is concerned with numerical analysis of cracked aircraft gas turbine engine (GTE) compressor disk based on plastic stre s intensity fa or (SIF) approa h. Dam ge accumulation nd growth at ope ation have occurred in slot fillet of disk a d blade attachment. In all of these f ilures, crack propagation started from p rt-trough quarter ellipti al corner sur ac flows. In order to determine elastic-plastic fracture resistance parameters full-size stress-strain state nalysis of compressor disk was performed for a quarter elliptical surface cracks under operation loading conditions. The process of numerical calculations includes the analysis of the elastic constraint parameters in the fo m f the non-singular T -stress and T Z – actor, as well as the elasti -plastic constraint parameters in the form of the local stress triaxiality h and I n -factor for the v ri us crack sizes and different operation temperatures. T e plastic SIF K p , which is hown to be sensitive to the constraint effects and environmental conditio s, offers a attractive option as self-dependent, unified paramet r for use in c aracterizi g th fracture resistance for a variety of aircraft GTE rotating components. © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. Keywords: Gas turbine engine; compressor disk; surface crack; plastic stress intensity factor. The GTE compressor disks are an integral component to a gas turbine assembly and their failures can lead to aircraft catastrophic damage. Shaniavski (1995) identified and listed the predominant failure mechanisms for gas turbine disks such as high cycle fatigue (HCF), low cycle fatigue (LCF), t ermo-mecha ical fatigue (TMF), environmental attack, © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. The GTE compressor disks are an integral component to a gas turbine assembly and their failures can lead to aircraft catastrophic damage. Shaniavski (1995) identified and listed the predominant failure mechanisms for gas turbine disks such as high cycle fatigue (HCF), low cycle fatigue (LCF), thermo-mechanical fatigue (TMF), environmental attack, Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation. Abstract 1. Introduction 1. Introduction

* Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt 2452-3216 © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. 2452-3216 © 2018 The Authors. Published by Elsevier B.V. Peer review under r sponsibility of the ECF22 o ganizers. * Corresponding author. +7-843-236-31-02; fax: +7-843-236-31-02. E-mail address: yarullin_r@mail.ru * Corresponding author. +7-843-236-31-02; fax: +7-843-236-31-02. E-mail ad ress: yarullin_r@mail.ru

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

2452-3216  2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. 10.1016/j.prostr.2018.12.170