PSI - Issue 5

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com S ienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Struc ural Integrity 5 (2017) 1153–1159 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2017) 000 – 000 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2017) 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. 2nd International Conference on Structural Integrity, ICSI 2017, 4-7 September 2017, Funchal, Madeira, Portugal Landing Gear Structural Health Monito ing (SHM) Chad Forrest a, *, Clint Forrest b , Doug Wiser c a ES3, Inc., 1346 Legend Hills Drive, Clearfield, Utah 84015, chad.forrest@es3inc.com b ES3, Inc., 1346 Legend Hills Drive, Clearfield, Utah 84015, clint.forrest@es3inc.com c ES3, Inc., 1346 Le end Hills Drive, Clearfield, tah 84015, doug.wiser@es3inc.com Abstract This paper provides information on the development of a landing gear Structural Health Monitoring (SHM) system that provides prognostic/diagnostic HUMS capabilities through direct load measurement in addition to strut servicing detection algorithms. The system provides advanced monitoring technology via the incorporation of new sensors integrated into the landing gear assembly. The direct load measurement approach is a paradigm shift from current methods of tracking fatigue damage of airframe landing gear systems and fuselag support structures, which depend on data collection of aircraft parameters recorded onboard at various sampling rates by SHM devices. The landing gear SHM provides direct loads measurement, weight/balance calculations, and the ability to perform Condition Based Maintenance (CBM) on the landing gear components. NAVAIR contracted with ES3 to support the development of the landing gear SHM via the Small Business Innovative Research (SBIR) program, via a Phase II award on the N121-043 topic. The proposed solution will be directly transferable to other Navy, military and commercial aircraft platforms. T is paper will address the following topics in the area of HUMS and CBM: (1) advanced landing gear sensors for direct load measurement; (2) dat fusion of direct loads monitoring data into fatigue life assessme ts; (3) paradigm shifts in aircraf maintenance utilizing strut servicing detection algorithms; (4) system verification and validation; and (5) safety and maintenance benefits. Prior work in the field of spectrum development and usage monitoring has typically focused on the aircraft structure, with assumptions translated to the landing gear components without any direct measurement. The benefits of usage monitoring can also be realized for landing gear. Direct loads measurement provides the ability to extend service life, remove components based on actual loading, improve safety, increase aircraft availability, and save maintenance costs with incorporation of CBM data into the maintenance practices. This paper advances the state-of-the-art via the miniaturization of sensors rated for the severe landing gear environment at a high Technological Readiness Level (TRL). 2nd International Conference on Structural Integrity, ICSI 2017, 4-7 September 2017, Funchal, Madeira, Portugal Landi g Gear Structural Health Monitoring (SHM) Chad Forrest a, *, Clint Forrest b , Doug Wiser c a ES3, Inc., 1346 Legend Hills Drive, Clearfield, Utah 84015, chad.forrest@es3inc.com b ES3, Inc., 1346 Legend Hills Drive, Clearfield, Utah 84015, clint.forrest@es3inc.com c ES3, Inc., 1346 Legend Hills Drive, Clearfield, Utah 84015, doug.wiser@es3inc.com Abstract This paper provides information on the development of a landing gear Structural Health Monitoring (SHM) system that provides prognostic/diagnostic HUMS capabilities through d rect load measurement in addition to strut servicing detection algorithms. The system provides advanced monitoring technology via the incorporation of new sensors integrated into the landing gear assembly. The direct load measurement approach is a paradigm shift from current methods of tracking fatigue damage of airframe landing gear systems and fuselage support structures, which depend on data collection of aircraft parameters recorded onboard at various sampling rates by SHM devices. The landing gear SHM provides direct loads measurement, weight/balance calculations, and the ability to perform Condition Based Maintenance (CBM) on the landing gear components. NAVAIR contracted with ES3 to support the development of the landing gear SHM via the Small Business Innovative Research (SBIR) program, via a Phase II award on the N121-043 topic. The proposed solution will be directly transferable to other Navy, mili ary and commercial ircr ft platforms. This paper wil address the following topics in the area o HUMS and CBM: (1) advanced landing gear sensors for direct load measurement; (2) data fusion of direct loads monitoring data into fatigue life assessments; (3) paradigm shifts in aircraft maintenance utilizing strut servicing detection algorithms; (4) system verification and validation; and (5) safety and maintenance benefits. Prior work in the field of spectrum development and usage monitoring has typically focused on the aircraft structure, with assumptions translated to the landing gear components without any direct measurement. The benefits of usage monitoring can also be realized for landing gear. Direct loads measurement provides the ability to extend service life, remove components based on actual loading, improve safety, increase aircraft availability, and save maintenance costs with incorporation of CBM data into the maintenance practices. This paper advances the state-of-the-art via the miniaturization of sensors rated for the severe landing gear environment at a high Technological Readiness Level (TRL). © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017 © 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.

2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. 2452-3216  2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017 10.1016/j.prostr.2017.07.025 2452-3216 © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. 2452-3216 © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. * Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt * Corresponding author. E-mail address: chad.forrest@es3inc.com * Corresponding author. E-mail address: chad.forrest@es3inc.com