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 Structural Integrity 14 (2019) 184–190 Available online at w .sciencedirect.com S c 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 o en access article under the CC BY-NC-ND license (https://creativecommons.org/li enses/by-nc-nd/4.0/) Selection and pe -revi w under responsibility of Peer-review under resp nsibility of the SICE 2018 organizers. 2nd International Conference on Structural Integrity and Exhibition 2018 Life extension of UAVs: a c se study of Indian UAVs Manu Jain*, S Rajashekar, R Vas tha, V Subrama ian, V Maharajan, V Ashok Rangan ADE, DRDO, New Tippasandra, Bangaluru-560 075, India Abstract Unmanned Aerial Vehicles (UAVs) are an integral part of any Armed force. They are being used in dull, dirty, dangerous and demanding missions. These missions restrict the life of UAV thus increasing the cost of UAV operations. To keep the operational cost low, it is essential to utilize UAVs to their full potential and life. The process of aging of UAV which results in structural and performance deterioration cannot be stopped, but its impact can be limited by using preventive measures, proper maintenance and implementing the required changes. A well-used UAV can be a befitting candidate for Life extension. Life extension of UAVs cannot be just on economic factors but also on reliability and performance in the extended life. This paper presents the case study of life extension of Indian UAVs which are designed and developed by Aeronautical Development Establishment, Bengaluru. These UAVs have been field tested and operationalized by Armed forces under varying environmental and usage conditions. The procedure, conditions and lessons learnt during the life extension process of UAVs are described. Life extension of these UAVs has resulted in considerable amount of cost and time saving to the users. Keywords: UAV; Non Destructive Testing (NDT); life extension 1. Introductio Operational and environmental factors lead to the life of a UAV to become limited. User demands that the UAVs be utilized for the maximum possible operations/tim . This leads to the requirement of in-service life extension programs, which is defined by Stevan Maksimović et al. (2015) as “The service life extension programs, for ext nding the ai craft service lif , consist of a process of defining and executing the recommended additional procedures as aircraft monitoring and maintenance with required possible additional constraints and limits for the further aircraft service during the period of extended life, with issuing the appropriate certificate for airworthiness”. 2nd International Conference on Structural Integrity and Exhibition 2018 Life extension of UAVs: a case study of Indian UAVs Manu Jain*, S Rajashekar, R Vasantha, V Subramanian, V Maharajan, V Ashok Rangan ADE, DRDO, New Tippasandra, Bangaluru-560 075, India Abstract Unmanned Aerial Vehicles (UAVs) are an integral part of any Armed force. They are being used in dull, dirty, dangerous and demanding missions. These missions restrict the life of UAV thus increasing the cost of UAV operations. To keep the operational cost low, it is essential to utilize UAVs to their full potential and life. The process of aging of UAV which results in structural and p rformance deterioration c not be stopped bu its impact can be limited by using preventive measures, proper maintenance and impl ment ng the required changes. A w ll-used UAV can be a befitting candidate for Lif extension. Life ext nsion of UAVs cannot be ju t on economic facto s but a so n reliability and performance in the extended life. his paper presen s the a e study of life extension of Indian UAVs which are designe and developed by Aeronautical Developm nt Establishment, Bengaluru. These UAVs have been fi ld test and operationalized by Armed forces und r varying environmental d usag conditions. The procedure, conditio s and lessons learnt during the life extension process of UAVs are described. Life xtension of these UAVs has resulted in considerable amount of cost nd time saving to the users. Keywords: UAV; Non Destructive Testing (NDT); life extension 1. Introduction Operational and enviro mental fac o s le d to life of a UAV to become limited. User demands that the UAVs be utiliz d for the maximum po sible operations/time. This leads to the requirement of in-s rvice life extension programs, which is defined by Stevan Maksimović et al. (2015) as “The service life extension programs, for extending the aircraft service life, consist of a process of defining and executing the recommended additional procedures as aircraft monitoring and maintenance with required possible additional constraints and limits for the further aircraft service during the period of extended life, with issuing the appropriate certificate for airworthiness”. * Man Jain. Tel.: +91-80-25057482 ; fax: +91-80-25057227. E-mail add ess: manujain@ade.drdo.in © 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.

* Manu Jain. Tel.: +91-80-25057482 ; fax: +91-80-25057227. E-mail address: manujain@ade.drdo.in

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.2019.05.024 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-r view under responsibility of Peer-review under responsibility of the SICE 2018 organizers. 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. * Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt