PSI - Issue 14

ScienceDirect Available online at www.sciencedirect.com Av ilable online at www.sciencedire t.com Sci ceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 14 (2019) 112–118 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 Available online at www.sciencedirect.com e Structural Integrity Procedia 00 (2018) 000 – 000

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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.2019.05.015 2452-3216 © 2018 The Authors. Published by Elsevier B.V. This is a 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 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 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 * Corresponding author. Tel.: 040-24188150; fax: 040-24348914. E-mail address: sameerkantbehera@asl.drdo.in 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 lice se (https://creativecommons.org/licenses/by- c-n /4.0/) Selection and peer-review under re ponsibility of Pe r-review under responsibility of the SICE 2018 organ zers. 2nd International Conference on Structural Integrity and Exhibition 2018 Structural Integrity Assessment of Filament Wound Composite Pressure Vessel Using Through Transmission Technique Sameerkant Behera a* , S. K. Sahoo b , Lokesh Srivastava c , A. S. Srinivasa Gopal d a, b, c, d Advanced System Laboratory, A. P. J. Abdul Kalam Missile Complex, P.O. Kanchanbagh, HYDERABAD, 500058, INDIA Abstract Filament wound composite pressure vessels are widely used as rocket motor case for space applications due to its high performance factor. High performance factor is attributed due to the fact that composite materials are having higher specific strength, high specific modulus and strength tailorability characteristics which results in reduction of weight of the structure. However composite structures are more prone to damage accumulation such as matrix cracking, delamination, de-bonding, porosity, fibre buckling, fiber breakage etc. which are encountered in entire manufacturing cycle. Timely and accurate detection of above damage throughout its service life is necessary to have a reliable structure. Here, a through transmission ultrasonic testing methodology has been established for detection of defect in large sized composite pressure vessel. In the last decade, many open literatures have been available on design, development and qualification of composite pressure vessels, however no comp ehensiv work is available on structural integrity assess ent using above said technique. This paper discusses on insight of various efect arised due to process pa ameter va iation during manufacturing an ts detection using through transmission ultrasonic technique. Further challenges multif ld due to la k of full roof ethodology and reference standards in pen source. Henc customized refer nce locks have be n made simulating defect such as delamination & simulating varying thickness and their ultrasonic responses have been characterized. Ultr sonic response on full scale composite pressure vessel was studied and finally an overview of structural integrity assessment of composite pressure vessel has been presented. Keywords: composite pressure vessel; structural integrity; through transmission; ultrasonic response; 1. Introduction Filament-wound composite pressure vessels are high-pressure container that are widely used as components of aerospace, hydrospace and military applications such as air bottles, pipe lines, rocket motor casings, helicopter blades, large storage tanks etc. [1]. Composite materials are increasingly being used because of their high specific strength, specific stiffness and strength tailorability charact ristics over their metal counterparts, as well as excellent corrosion and fatigue resistance [5]. Filament winding is an obvious choice to develop pressure vessel as it provides an efficient netting system of fibers /roving, in which the benefit of variability of directional strength is utilized [4]. However composite structures are process intensive and more prone to damage accumulation due to matrix cracking, delamination, fibre-matrix de-bonding, porosity, fiber breakage etc. which are encountered during entire manufacturing cycle. When structures are designed with marginal factor of safety and end application is of single shot based, it is highly imperative to have timely and accurate detection of above damages throughout its service life. Therefore, non destructive techniques are of utmost importance to monitor the health of the structure and assess structural integrity of composite pressure vessel. In this paper, a through transmission ultrasonic testing methodology has been established for large sized composite pressure vessel. A reference sample has been made simulating defect such as delamination and its ultrasonic response has been characterized. Ultrasonic response on full scale product level has been studied with respect to reference sample. Finally an overview 2nd International Conference on Structural Integrity and Exhibition 2018 Structural Integrity Assessment of Filament Wound Composite Pressure Vessel Using Through Transmission Technique Sameerkant Behera a* , S. K. Sahoo b , Lokesh Srivastava c , A. S. Srinivasa Gopal d a, b, c, d Advanced System Laboratory, A. P. J. Abdul Kalam Missile Complex, P.O. Kanchanbagh, HYDERABAD, 500058, INDIA Abstract Filament wound composite pressure vessels are widely used as rocket motor case for space applications due to its high performance factor. High performance factor is attributed due to the fact that composite materials are having higher specific strength, high specific modulus and strength tailorability characteristics which results in reduction of weight of the structure. However composite structures are more prone to damage accumulation such as matrix cracking, delamination, de-bonding, porosity, fibre buckling, fiber breakage etc. which are encountered in entire manufacturing cycle. Timely and accurate detection of above damage throughout its service life is necessary to have a reliable structure. Here, a through transmission ultrasonic testing methodology has been established for detection of defect in large sized composite pressure vessel. In the last decade, many open literatures have been available on design, development and qualification of composite pressure vessels, however no comprehensive work is available on structural integrity assessment using above said technique. This paper discusses on insight of various defect arised due to process parameter variation during manufacturing and its detection using through transmission ultrasonic technique. Further challenges multifold due to lack of full proof methodology and reference standards in open source. Hence customized reference blocks have been made simulating defect such as delamination & simulating varying thickness and their ultrasonic responses have been characterized. Ultrasonic response on full scale composite pressure vessel was studied and finally an overview of structural integrity assessment of composite pressure vessel has been presented. Keywords: composite pressure vessel; structural integrity; through transmission; ultrasonic response; 1. Introduction Filament-wound composite pressure vessels are high-pressure container that are widely used as components of aerospace, hydrospace and military applications such as air bottles, pipe lines, rocket motor casings, helicopter blades, large storage tanks etc. [1]. Composite materials are increasingly being used because of their high specific strength, specific stiffness and strength tailorability characteristics over their metal counterparts, as well as excellent corrosion and fatigue resistance [5]. Filament winding is an obvious choice to develop pressure vessel as it provides an efficient netting system of fibers /roving, in which the benefit of variability of directional strength is utilized [4]. However composite structures are process intensive and more prone to damage accumulation due to matrix cracking, delamination, fibre-matrix de-bonding, porosity, fiber breakage etc. which are encountered during entire manufacturing cycle. When structures are designed with marginal factor of safety and end application is of single shot based, it is highly imperative to have timely and accurate detection of above damages throughout its service life. Therefore, non destructive techniques are of utmost importance to monitor the health of the structure and assess structural integrity of composite pressure vessel. In this paper, a through transmission ultrasonic testing methodology has been established for large sized composite pressure vessel. A reference sample has been made simulating defect such as delamination and its ultrasonic response has been characterized. Ultrasonic response on full scale product level has been studied with respect to reference sample. Finally an overview * Corresponding author. Tel.: 040-24188150; fax: 040-24348914. E-mail address: sameerkantbehera@asl.drdo.in 2nd International Conference on Structural Integrity and Exhibition 2018 tructural Integrity Assess ent of Filament ound Composite Pressure essel sing hrough rans ission echnique Sa eerkant Behera a* , S. K. Sahoo b , Lokesh Srivastava c , A. S. Srinivasa Gopal d a, b, c, d Advanced System Laboratory, A. P. J. Abdul Kalam Missile Complex, P.O. Kanchanbagh, HYDERABAD, 500058, INDIA Abstract Filament wound composite pressure vessels are widely used as rocket motor case for space applications due to its high performance factor. High performance factor is attributed due to the fact that composite materials are having higher specific strength, high specific modulus and strength tailorability characteristics which results in reduction of weight of the structure. However compo ite structures are more prone to damage accu ulati n such as matrix cracking, d lamination, de-bonding, porosity, fibr buckling, fiber breakage etc. w ic are encount red in entire manufacturing ycle. Timely and accurate detection f ab ve damag th oug out its service lif is necessary to ha e a reliable structure. Here, a through transmission ultrasonic testing methodology has been established for detection of defect in large sized composite pressure vessel. In the last decade, many open literatures have been available on design, development and qualification of composite pressure vessels, however no comprehensive work is available on structural integrity assessment using above said technique. This paper discusses on insight of various defect arised due o process parameter variation during manufacturing and its detection using through transmission ultrasonic technique. Further challenges multifold due to lack of full proof methodology and reference standards in open source. Hence customized reference blocks have been made simulating defect such as delamination & simulating varyi g thickness and their ultrasoni responses have been characterized. Ultrasonic response on full s ale composite pressure vessel was st died a d fi ally an overview of structural integrity assessment of composit pressure vessel has been present d. Keywords: composite pressure vessel; structural integrity; through transmission; ultrasonic response; 1. Introduction Filament-wound composite pressure vessels are high-pressure container that are widely used as components of aerospace, hydr spa e and military applications such as air bottles, pip n s, rocket motor casings, helicopter blades, large storage tanks etc. [1]. Composite materials are increasingly being used because of their high specific strength, specific stiffness and strength tailorability characteristics over their m tal counterparts, as well as excelle t corrosion and fatigue resistance [5]. Filament winding is an obvious choice to develop pre sur vessel as it provides an efficient netting system of fibers /roving, in which the benefit of variability of direction l strength is utilized [4]. However composite structures are process intensiv and more prone to damage accumulation due to matrix cracking, delamination, fibr -matrix de-bonding, porosity, fiber breakage etc. which are e cou tered during entire manufacturing cycle. hen structures are designed with marginal factor of safety and end application is of single shot based, it is highly imperative to have mely and accurate detection of above damages throughout ts service life. Therefore, non destructive techniques re of utmost importa ce to monitor the health of the structure and assess structural integrity of c mposite pressure vessel. In this paper, a through transmission ultra onic testing methodology has been established for large sized composite pressure vessel. A reference sample has been made simulating defect such as delamination and its ultrasonic response has been characterized. Ultrasonic response on full sc le pr duct level as been studied with respect to reference sample. Finally an verview * Corresponding author. Tel.: 040-24188150; fax: 040-24348914. E-mail address: sameerkantbehera@asl.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.