PSI - Issue 14

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 14 (2019) 634–641 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2018) 000–000 Available online at www.sciencedirect.com ScienceDirect Structural Integrity 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. © 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. 2nd International Conference on Structural Integrity and Exhibition 2018 Blast response of Hollow glass (H-glass) fibre reinforced epoxy matrix composites C.Jayarami Reddy*, B.Venkataramudu, G.Seshagiri Rao, K.Gopinadha Reddy, Rajesh Kumar, Ranjit Kumar Singh, V.Madhu Armour Design and Development Division, Defence Metallurgical Research Laboratory, Hyderabad, India Abstract The studies on response of materials against explosive blast loads have enormously increased in the recent years due to the increased blast incid s across the globe. Few studies hav been rep rted on the blast performance of gl s fibre reinforced composites. However, no studies were reported on the response of the Hollow glass (H- glass) fibre reinforced polymer composites against explosive blast loads. The present paper focuses on the experimental investigation of the response of the H- glass/epoxy composite laminates against air blast loading. The explosive loading on 5mm thick composite laminates at both 300mm and 400mm stand-off distances (SoD) was generated by detonating 142 gms of plastic explosive. The incident and reflected pressures at both the SoDs were recorded using piezo-electric pressure sensors. H-glass composites exhibited mode-I failure (large in-elastic deformation) at both SoDs, whereas E-glass composites showed mode –I failure at 300mm SoD only. The change in failure modes of composites with change in SoD was also discussed. The blast performance of the H-glass composite was compared with the performance of the solid glass fibre (E-glass) composites. © 2018 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licens s/by-nc-nd/4.0/) Sel tion and peer-review under responsibility of Peer-r view under responsibility of the SICE 2018 organizers. Keywords: H-glass; composi es; airb ast; failure meachanisms; 2nd International Conference on Structural Integrity and Exhibition 2018 Blast response of Hollow glass (H-glass) fibre reinforced epoxy matrix composites C.Jayarami Reddy*, B.Venkataramudu, G.Seshagiri Rao, K.Gopinadha Reddy, Rajesh Kumar, Ranjit K mar Singh, V.Madhu Armour Design and Development Division, Defence Metallurgical Research Laboratory, Hyderabad, India Abstract The studies on response of ma erials against explosive blast loads have en mously incr ased in the recent yea s due to the increased blast incidents across the globe. Few studies have been report d on the bl t perform nce of glass ibr reinforc d . Howev r, no studies were reported o the esponse f Hollow gl ss (H- l ss) fibre reinf rced polymer composites against explosive blast load . The present paper focuses on th experime tal invest gation of the respo se of he H glass/epoxy composite laminates again t air blast loadi g. The explosive loading on 5mm thick composit laminates at both 300mm and 400mm stand-off distanc s (SoD) was ge erat d by detonating 142 gms of plastic explosiv . The inci ent and ref ected pr ssures at both the S Ds were rec rded using piezo-ele tric pres ure sensors. H-glass composites exhibited mode-I failure (large in- lastic deformati n) at bo SoDs, whereas E-glass compo it s showed mod –I failur at 300mm SoD nly. Th change in failure mod s of co posites with change in SoD was al o discus ed. The blast performance of the H-glass composite was compared with the performance of the solid glass fibre (E-glass) composites. © 2018 The Authors. Published by Elsevier B.V. This is an open acce s rticle un r the CC BY-NC-ND lic ns (https://creativecommons.org/licenses/by-nc-nd/4.0/) Selection and pe r-r view under responsib lity of P er-review und r respons bility of t e SICE 2018 organizers.

Keywords: H-glass; composites; airblast; failure meachanisms;

© 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.: +91-40-2458 8012; fax: +91-40-2454 8504. E-mail address: cjrreddy78@gmail.com * Correspon ing author. Tel.: +91-40-2458 8012; fax: +91-40-2454 8504. E-mail address: cjrreddy78@gmail.com

2452-3216 © 2018 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. 2452-3216 © 2018 The Authors. Published by Elsevier B.V. This is a open access article und r the CC BY-NC-ND lic nse (https://creat vecommons.org/licenses/by- c-nd/4.0/) Selection and peer-review under responsibility of Peer-review under responsibility of the SICE 2018 organizers.

* 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.2019.05.078