PSI - Issue 14

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www.elsevier.com/locate/procedia 2 nd International Conference on Structural Integrity and Exhibition 2018 Investigation of Shot Peening Effect on Titanium Alloy Affecting Surface Residual Stress and Roughness for Aerospace Applications R.K. Kumar a , P. SampathKumaran b , S. Seetharamu c , S. Anand Kumar d* , T. Pramod e , G.J. Naveen f a Central Power Research Institute (CPRI), Bangalore 560080, India b,c National Design and Research Forum (NDRF), Bangalore 560001, India d Indian Institute of Technology Jammu (IIT-Jammu), Jammu & Kashmir181 221, India Abstract Titanium (Ti) alloys are used in aviation industry such as engine parts, air frames etc. The main advantage of using Ti alloy is to combat chemical attack in corrosive and hash environment as well as fatigue resistance under cyclic loading conditions. This investigation mainly focuses on how to improve the fatigue resistance of a component thereby the life improvement is envisaged. One of the methods employed is shot peening process, which is a surface phenomenon and introduces compressive residual stress so that the properties like stress corrosion cracking, for ing operations, strength get enhanced. The design and experimental work involves the various shot peening parameters such as impact angle, cov rage area, Alme intensity levels affecting the surface roughness as well as surface and sub-surfac residual stresses. Further, design of experiments involving Taguchi’s technique has been discussed at length. The shot pe ning parame ers have been correlated with residual stress and surface roughness parameters. It is also observed that microstructure of the titanium alloy is h ving e featur s to support the fatigue properties. Finally the work has be n summarized to rise at optimization of these parameters to achieve higher residual stress from the point of high fatigu life. © 2018 R.K. Kumar, P. SampathKumaran, S. Seetharamu, S. Anand Kumar, T. Pramod, G.J. Naveen. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0/) Selection and peer-review under responsibility of Peer-review under responsibility of the SICE 2018 organizers. 2 nd International Conference on Structural Integrity and Exhibition 2018 Investigation of hot Peening Effect on Titanium Alloy Affecting Surface Residual Stress and Roughness for Aerospace Applications R.K. Kumar a , P. SampathKumaran b , S Seetharamu c , S. Anand Kumar d* , T. Pramod e , G.J. Naveen f a Central Power Research Institute (CPRI), Bangalore 560080, India b,c National Design and Research Forum (NDRF), Bangalore 560001, India d I di n I stitute of Technology Jammu (IIT-Jammu), Jammu & Kashmir181 221, India e The Energy and Resources Institute (TERI), Bangalore 560071, India f Sambhram Institute of Technology (SaIT), Bangalore 560091, India Abstract Titanium (Ti) alloys are s d i aviati n industry such as ngine parts, air fra es etc. The main advantage f usi g Ti alloy is to combat che ical attack in corro ive and hash environment a well s fatigue r sistance u der cycli loading conditions. Thi investigation mainly focu es n how to improve the fatigue resistance of a omponent thereby the lif mprovement is visaged. One of the methods employ d is shot peening process, which is a surf ce phenom non and int oduces compressive residual stress so that the prop rtie like stress corrosion cracking, forming operatio s strength g t enhanced. The des gn nd experime tal work involve the various sh t p ening parameters such a impact a gle, c v rage a a, Almen inte s ty levels affecting the surf ce roughness as w ll a surface and sub-surface res du l stresses. Further, des gn of experiments involving Tagu hi’s technique has been discussed t leng h. Th hot peening p rameters h ve be n c rrelat d w t residual stress and surfac r ughness parameters. It is also observed that microstructure of the titanium alloy is having the features to support the fatigue properties. Finally the work has been summarized to arise at optimization of these parameters to achieve higher residual stress from the point of higher fatigue life. © 2018 R.K. Kumar, P. SampathKumaran, S. Seetharamu, S. Anand Kumar, T. Pra d, G.J. Naveen. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0/) Selection and peer-review under responsibility of Peer-review under responsibility f t e SICE 2018 organizers. 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. e The Energy and Resources Institute (TERI), Bangalore 560071, India f Sambhram I stit te of Technology (SaIT), Bangalore 560091, India © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. © 2019 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0/) Selection and peer-review under responsibility of Peer-review under responsibility of the SICE 2018 organizers. Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation. Keywords: Shot Peening, Design of Experiments, Almen Intensity, Residual Stress, Surface Roughness Keywords: Shot Peening, Design of Experiments, Almen Intensity, Residual Stress, Surface Roughness 2452-3216 © 2018 R.K. Kumar, P. SampathKumaran, S. Seetharamu, S. Anand Kumar, T. Pramod, G.J. Naveen. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0/) Selection and peer-review under responsibility of Peer-review under responsibility of the SICE 2018 organizers. 2452-3216 © 2018 R.K. Kumar, P. SampathKumaran, S. Seetharamu, S. Anand Kumar, T. Pramod, G.J. Naveen. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0/) Selection a peer-review under responsibility of Peer-review under responsibility of the SICE 2018 organizers. * Corresponding author: S. Anand Kumar; Tel.: +91-9036624149. E mail address: anand.subramaniyan@iitja mu.ac.in & an ndk marait@gmail.com * Corresponding author: S. Anand Kumar; Tel.: +91-9036624149. E-mail address: anand.subramaniyan@iitjammu.ac.in & anandkumarait@gmail.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  2019 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0/) Selection and peer-review under responsibility of Peer-review under responsibility of the SICE 2018 organizers. 10.1016/j.prostr.2019.05.018