PSI - Issue 2_A

ScienceDirect Available online at www.sciencedirect.com Av ilable online at ww.sciencedire t.com ScienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Struc ural Integrity 2 (2016) 1506–1513 Available online at www.sciencedirect.com Sci nceDirect StructuralIntegrity Procedia 00 (2016) 000–000 Available online at www.sciencedirect.com ScienceDirect StructuralIntegrity Procedia 00 (2016) 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. 21st European Conference on Fracture, ECF21, 20-24 June 2016, Catania, Italy Formation of composite layers TiNiZr-cBN-Co, working in conditions of cyclic loading and reverse friction Rusinov P.O. a *, Blednova Zh.M. a , Balaev E.U. a , DmitrenkoD.V. a a Kuban State Technological University, Moskovskaya 2, Krasnodar 350072, Russia Abstract For the composite construction of the surface layer, we carried out the selected composition materials, methods and means of formation. multilayer composition "steel - material with shape memory eff ct (SME) - we rproof layer» (TiNiZr - cBN-Co) was obtained by high-velocityoxy-fuel spraying in a vacuum. The sequence of functional layers’deposition, their composition, thickness, structure-phase state and dispersity were determined by operating conditions and are controlled by the processing modes. To enhance the survivability and longevity,it is recommended to form the SME layer so that its temperature, given the increase in friction, correspondedto the martensitic state and had increased relaxation and damping capacity in order to slow down cracking. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. Keywords: composite materials, shape memory effect, high-velocity oxy-fuel spraying, cycle fatigue, wear resistance ; 1. Introduction Due to the recent expansion of the man facturing capacity, multicomponent and multilayer structures, including layered coatings, are increasingly considered as a new reserve to increase functional reliability of products. It is known that smart materials with shape memory effect (SME) have a wide range of features. Their use in the formation of the layered composite surface layers can be very productive, providing wide range of sought-after features: superelasticity, wear and corrosion resistance, high damping capacity, durability, crack resistance, adaptability. 21st European Conference on Fracture, ECF21, 20-24 June 2016, Catania, Italy Formation of composite layers TiNiZr-cBN-Co, working in conditions of cyclic loading and reverse friction Rusinov P.O. a *, Blednova Zh.M. a , Balaev E.U. a , DmitrenkoD.V. a a Kuban State Technological University, Moskovskaya 2, Krasnodar 350072, Russia Abstract For the composite construction of the surface layer, we carried out the selected composition materials, methods and means of formation. A multilayer composition "steel - material with shape memory effect (SME) - wearproof layer» (TiNiZr - cBN-C ) was obtained by high-vel city xy-fuel spraying in vacuum. The sequence of functional layers’deposition, their composition, thickness, structure-phase state and dispe sity were determined by operating conditi s and are controlled by the processing modes. To enhanc t e urvivability and longevity,it is recommended to form the SME layer so that its t mpera ure, giv n the increase in friction, correspondedto the martens ic state and had increased relaxation and damping capacity in o der to slow down cracking. © 2016 The Authors. Published by Elsevier B.V. Peer-review under esponsibility of the Scientific Committee of ECF21. Keywords: composite materials, shape memory effect, high-velocity oxy-fuel spraying, cycle fatigue, wear resistance ; 1. Introduction Due to th r cent expansion of the manufacturing capacity, multicomponent and multilayer structures, including layered oating , are increasi gly considered as a n w reserve to ncrease functional re iability of products. It is known that smart materials with shape m mory effect (SME) have a wide range of fe tures. Their use in he formation of the layer d composite surfac layers can be very productive, providing wide ange of sought-after eatures: super lasticity, wear and corrosion re ist ce, high damping capac ty, durability, crack resis anc , ad ptability. Copyright © 2016 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 ECF21. © 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.

* Corresponding author. Tel.: +7-905-495-1555 ; fax: +7-861-253-4997 . E-mail address: ruspiter5@mail.ru * Corresponding author. Tel.: +7-905-495-1555 ; fax: +7-861-253-4997 . E-mail ad ress: r spiter5@mail.ru

* 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 ECF21. 2452-3216© 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21.

2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Copyright © 2016 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 ECF21. 10.1016/j.prostr.2016.06.191