PSI - Issue 14

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at www.sciencedire t.com cienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structural Integrity 14 9 89–95 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

www.elsevier.com/locate/procedia www.elsevier.com/locate/procedia

www.elsevier.com/locate/procedia

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 Evaluation of structural integrity of tactical missile ceramic radomes und combined thermal and structural loads S. Narendar a, *, R. Gopikrishna b a TSTF, Defence Research and Development Laboratory, Kanchanbagh, Hyderabad 500 058, Telangna State b SSTC, Defence Research and Development Laboratory, Kanchanbagh, Hyderabad 500 058, Telangana State Abstract Radome is a thermo-structural member used in tactical missiles and houses the avionic systems like seeker. It is subjected to severe thermal as well as structural loads during the flight. The material of the radome is chosen such that it is transparent electromagnetic radiation. The ceramic radome is attached to the metallic bulkhead with high temperature glue. In the present manuscript, the experimental evaluation methodology implemented for evaluation of the structural integrity of the ceramic radome under combined thermal and structural loads is presented. Initially axial load, to simulate the resultant drag force and a distributed lateral load, to simulate the bending moment, are applied via a pre-casted contoured Teflon mock sections, up to proof load and then time varying temperature is applied. The time-varying temperature profile is applied via a closed loop control based on PID and the heating environment is created using short wave infra-red rad ation. Exhaustive instrument tion is used in th experiments. Detailed results are also presented in the ma uscript up to t e tructural failure. © 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: Ceramic Radome; Thermal-Structural Test; PID Control; Infrared Heating; Closed-Loop Control. 2nd International Conference on Structural Integrity and Exhibition 2018 Evaluation of structural integrity of tactical missile ceramic radomes under combined thermal and structural loads S. Narendar a, *, R. Gopikrishna b a TSTF, efence esearch and Develop ent aboratory, Kanchanbagh, Hyderabad 500 058, Telangna State b SSTC, Defence Research and Development Laboratory, Kanchanbagh, Hyderabad 500 058, Telangana State Abstract Radome is a thermo-structural member u ed in tactical missiles and houses the avionic sy tems like seeker. It is subjected to seve e thermal as well as structu l loads during the fligh . T a er al of t radome is chosen such that it is ranspar electromagnetic radiat on. The ceramic radome is attached to the metallic bu khead with high temperatur glue. In the p esent manuscript, the experimental ev luation methodology implemented for evaluati n of the structural integri y of the ceramic radome under combined thermal and structural loads is p sented. In tially axi l load, to simulate the resultant drag force and a distributed lateral load, to simulat the b nding moment, are applied via a pre-c sted contoured Tef on mock sections, u to pro f load and then time varying tempe atur is appl ed. The time-varying temp rature profile is ppl ed via a closed loop con rol based on PID and t e h ating environment is created sing short wave infra-red radiation. Exhaust v ins rum ntation is used in the xperime ts. Detailed results are also presented in the manuscript up to the structural failure. © 2018 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (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. Keywords: Ceramic Radome; Thermal-Structural Test; PID Control; Infrared Heating; Closed-Loop Control.

1. Introduction

© 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. 1. Introduction

Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation. The radome is a portmanteau of radar and dome. The function of the radome is to protect the antenna from The word radome is a portmanteau of radar and dome. The function of the radome is to protect the antenna from

* Corresponding author. Tel.: +91 88976 25977; fax: +9140 2434 2309. E-mail address: narendar@drdl.drdo.in, nanduslns07@gmail.com * Correspon ing author. Tel.: +91 88976 25977; fax: +9140 2434 2309. E-mail address: narendar@drdl.drdo.in, nanduslns07@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.2019.05.012