PSI - Issue 14

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at www.sciencedire t.com Sci ceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 14 (2019) 556–563 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 Determination of optimal coupling stiffness using modal updating t chniques for Stiffened Plates K.Shrivastava a *, K.Vijayan a , V.Arora b a Dept. of Ocean Engineering and Naval Architecture, IIT Kharagpur, Kharagpur - 721302, India b ITI, SDU Mechanical Engg, Campusvej 55, 5230 Odense M, Denmark Abstract Stiffened structures are often utilized as structural members for numerous applications in various fields of engineering like Civil, Automobiles, Naval, Aerospace, etc. Thus analyzing stiffed structure for their structural integrity become pivotal. Simplest instance of a stiffened structure could be a plate with a beam acting as a reinforcement. The presented study focuses on Modal analysis of a stiffened plate comprising of a base plate and a beam attached to it in the longitudinal direction. Numerical analysis is carried out by formulating a FE model for the beam and plate. The plate and beam elements are coupled using discrete spring element. The capability of the model is verified by comparing the natural frequencies obtained through experimental techniques. A numerical based model updating was carried out to determine the optimal spring stiffness using Latin hypercube sampling. The optimal values of the spring stiffness were det rmined which reduced the rror in th natural freque c es. © 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. Keywords: Stiffened Plates; Modal Analysis; Model Updating 1. Introduction A major caus of structural failure could be attributed to structural vibration. In order to ensure the structural integrity of any body when subjected to harmful vibration, it is important to know its modal properties. These properties define the charact ristics and behavior of the structure under dynamic conditions. 2nd International Conference on Structural Integrity and Exhibition 2018 Determination of optimal coupling stiffness using modal updating techniques for Stiffened Plates K.Shrivastava a *, K.Vijayan a , V.Arora b a Dept. of Ocean Engineering d Naval Architectur , IIT Kharagpur, Kharagpur - 721302, India b ITI, SDU Mechanical Engg, Campusvej 55, 5230 Odense M, Denmark Abstract Stiffened structures are often utilized as structural members for numerous applications in v rious fields of engineering like Civil, Au omobiles, Naval, Ae ospace, etc. Thus analyz ng stiffed structure for their struc ural integrity become pivotal. Simplest i stance sti f structure could be a pl t with be m cting s a reinforcem nt. The presented study focuses on Modal analys s of a stiffened plate comprising of a bas pl te a beam attached to it in the longitudinal direction. Numeri al analysis is carried out by formulating a FE model for the beam and pla e. The plate and beam elements are coupled using discrete spring element. The c pability of the model is verified by comparing th natural frequencies obtained through experim ntal techniques A n merical bas d mod l updating wa car ied out t determine the optimal sp ing stiffness using Lat hy cube sampl ng. Th opt mal values of the p ing st ffness were determined which reduced the rror in the natu al frequencies. © 2018 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND lic nse (https://creativecommons.org/licenses/by- c-nd/4.0/) Selection and peer-review under responsibility of Peer-review under responsibility of the SICE 2018 organizers. Keywords: Stiffened Plates; Modal Analysis; Model Updating 1. Introduction A maj r cause f structural failure c uld be attributed to structural vibrati n. In order t ensu e the structural integri y of any body whe subjected to harmful vibration, it is import nt to k ow it modal properties. These properties define the characteristics and behavior of the structure under dynamic conditions. © 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.: +91-3222-282283; fax: +91-3222-255303. E-mail address: krshrivastava@iitkgp.ac.in * Correspon ing autho . Tel.: +91-3222-282283; fax: +91-3222-255303. E-mail address: krshrivastava@iitkgp.ac.in

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.2019.05.068