PSI - Issue 1

ScienceDirect Procedia Structural Integrity 1 (2016) 106–109 Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com Sci ceDirect Structural Integ ity Procedia 00 (2016) 000 – 000

www.elsevier.com/locate/procedia XV Portuguese Conference on Fracture, PCF 2016, 10-12 February 2016, Paço de Arcos, Portugal F-16 Wing Structure Lifecycle Paul F Braden a University of Utah, Salt Lake City, USA A o Paul F Braden 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. XV Portuguese Conference on Fracture, PCF 2016, 10-12 February 2016, Paço de Arcos, Portugal F-16 Wing Structure Lifecycle Paul F Braden a a University of Utah, Salt Lake City, USA Disclaimer The views expressed in this academic research paper are those of the author and do not reflect the official policy or position of the US government or the Department of Defense. In accordance with Air Force Instruction 51-303, it is not copyrighted, but is the property of the United States government. Abstract The most widely used military aircraft in existence today, the Lockheed Martin F-16 Falcon, has provided a standard baseline for small fighter jet lifecycle structural integrity studies. Due to the high stress environment of combat flight, the lifecycle analysis of the F-16 provides key insight into design considerations for future aircraft. The United States Air Force is already using the analysis done on the F-16 Falcon on newer fighter aircraft such as the Lockheed Martin F-22 and F-35 t carry ov r th lessons learned from this very successful programme. In this analysis, real- life data ollected from twenty years of the Air Force’s Aircraft Structu al Integrity Program (ASIP) is reviewed to highlight th most important advances in the structure of F-16. In ord r to focus on the most stre sed part of th aircraft, the analysis is only done on the wings. First, the F-16 crack database (CIRE) is reviewed to find the most common locations on the wing where cracking occurs. Next, certain exceptional cases are considered in order to understand unusual b havior. T en, th most detrimental cracks are analyzed to discuss potential risks if minimal repairs are done. After this, the design repairs for permanently reversing and preventing future cracks are reviewed to show effectiveness. Finally, predictions are made on the lifecycle and future areas of structural concern for the F-16 wing. © 2016 The Authors. Published by Elsevier B.V. XV Portuguese Conference on Fracture, PCF 2016, 10-12 February 2016, Paço de Arcos, Portugal F-16 Wing Structure Lifecycle Paul F Braden a a University of Utah, Salt Lake City, USA Disclaimer The views xp essed in this cademic res arch paper are those of the author and do not reflect the official pol cy or position of the US government or the Department of Defense. In accordance with Air Force Instruction 51-303, it is not copyrighted, but is the property of the United States government. Abstrac The most widely used mil tary aircraft in existe ce today, the Lockhe d Martin F-16 Falcon, h s provided a standard baseli e for sm ll fighter jet lifecycle structural int grity studies. Due to the hig str ss environme t of combat flight, the lifecycle analysi of th F-16 provides key insight into design consideratio s for future aircraft. The United States Air Force is already using the analysis done on the F-16 Falco on newer fight r aircraft suc as the Lockheed Martin F-22 and F-35 to carry over the lessons learn from t is very successful programme. In this analysis, real- life data collected from twenty years of the Air Force’s Aircraft St uctural Integrity Program (ASIP) is reviewed to highlight the most important dvanc s in the structure f the F-16. In ord r to focus on the most stressed part of t e aircraft, the analy is is only done on the wi gs. First, the F-16 crack dat base (CIRE) is reviewed to find th most common locations on the wi g where c acking occurs. Next, certain exceptional cases are considered n order to understand unu ual behavi r. Then, the most detrimental cracks are nalyzed to discuss potential risks if minimal repairs are done. After this, the design repairs for permanently reversing and preventing future cracks are reviewed to show effectiveness. Finally, predictions are made on the lifecycle and future areas of structural concern for the F-16 wing. © 2016 The Authors. Published by Els vier B.V. Disclaimer The views expressed in this academic research paper are those of the author and do not reflect the official policy or position of the US government or the Department of Defense. In accordance with Air Force Instruction 51-303, it is not copyrighted, but is the property of the United States government. Abstract The most widely used military aircraft in existence today, the Lockheed Martin F-16 Falcon, has provided a standard baseline for small fighter jet lifecycle structural integrity studies. Due to the high stress environment of combat flight, the lifecycle analysis of the F-16 provides key insight i to design considerations for future aircraft. The United States Air Force is al eady usi g he analysis done on the F-16 Falcon o newer fighter aircraft such as the Lock eed Martin F-22 and F-35 to carry ver the l ssons learned from this very successful programme. In this analysis, real- life data collected from twenty years of the Air Force’s Aircraft Structural Integrity Program (ASIP) is reviewed to highlight the most important advances in the structure of the F-16. In order to focus on the most stressed part of the aircraft, the analysis is only done on the wings. First, the F-16 crack database (CIRE) is reviewed to find the most common locations on the wing where cracking occurs. Next, certain exceptional cases are considered in order to understand unusual behavior. Then, the most detrimental cracks are analyzed to discuss potential risks if minimal repairs are done. After this, the design repairs for permanently reversing and preventing future cracks are reviewed to show effectiveness. Finally, predictions are made on the lifecycle and future areas of structural concern for the F-16 wing. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. a i it f t , lt it , U i i t i i earch paper are those of the aut t l t t i i l li iti t t t t t . it i t ti , it i t i t , t i t t f t it t t t. T t , , r . , o n . United States Air Force is already using the . a , . o , . , ( . , c n . h , m . , s e . , r . . li l i . . view under resp i ili i i i i . Copyright © 2015 The Authors. Published by Elsevier . . This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/). Peer-review under responsibility of the Scientific Committee of PCF 2016. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Peer-review under responsibility of the Scientific Committee of PCF 2016. Keywords: Structural Analysis, fracture, crack propagation, lifecycle, fatigue Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation. Keywords: Structural Analysis, fracture, crack propagation, lifecycle, fatigue P er-review under responsibility of h S ientific Comm ttee of PCF 2016. 2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Copyright © 2015 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license ( http://creativecommons.org/licenses/by-nc-nd/4.0/ ). Peer review under responsibility of the Scientific Committee of PCF 2016. 10.1016/j.prostr.2016.02.015 Distribution A: Ap roved for public release; distribution is unlimited * Corresponding author. Tel.: +0-000-000-0000 ; fax: +0-000-000-0000 . E-mail address: paulbraden11@gmail.com Distribution A: Approved for public release; distribution is unlimited * Co responding author. Tel.: +0-000-000-0000 ; fax: +0-000-000-0000 . E-mail address: paulbrad n11@gmail.com Distribution A: Approved for public release; distribution is unlimited * Corresponding author. Tel.: +0-000-000-0000 ; fax: +0-000-000-0000 . E-mail address: paulbraden11@gmail.com D i t . l.: ; : . * Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt A c mmon story about the F-16 Falcon fighter jet is the first flight on 20 January, 1974. The test pilot experienced some difficulties with the roll control that caused the plane to respond too strongly. As a result, the plane rolled so much during take- ff that the left horizontal stabilizer actually hit the runway. A common story about the F-16 Falcon fighter jet is the first flight on 20 January, 1974. The test pilot experienced some difficulties with the roll control that caused the plane to respond too strongly. As a result, the plane rolled so much during take-off that the left horizontal stabilizer actually hit the runway. n story about the F-16 Fa e r n A common story about the F-16 Falcon fighter jet is the first flight on 20 January, 1974. The test pilot experienced some difficulties with the roll control that caused the plane to respond too strongly. As a result, the plane rolled so much during take-off that the left horizontal stabilizer actually hit the runway. 1. Introduction 1. Introduction 1. Introduction Keywords: Structural Analysis, fracture, crack propagation, lifecycle, fatigue K , , , ,