PSI - Issue 2_B

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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. 21st European Conference on Fracture, ECF21, 20-24 June 2016, Catania, Italy Synthesis of crack initiation life in steel notched specimens under torsional fatigue based on the averaged strain energy d nsity Filippo Berto a,b , Alberto Campagnolo c , Giovanni Meneghetti c *, Keisuke Tanaka d a University of Padova, Department of Management and Engineering, Stradella S. Nicola 3, 36100, Vicenza (Italy) b NTNU, Department of Engineering Design and Materials, Richard Birkelands vei 2b, 7491, Trondheim, (Norway) c University of Padova, Department of Industrial Engineering, Via Venezia 1, 35131, Padova (Italy) d Meijo University, Department of Mechanical Engineering, 468-8502, Nagoya (Japan) Abstract The torsional fatigue behaviour of circumferentially notched specimens made of austenitic stainless steel, SUS316L, and carbon steel, SGV410, characterized by different notch root radii has been recently investigated by Tanaka. In that contribution, it was observed that the total fatigue life of the austenitic stainless steel increases with increasing stress concentration factor for a given applied nominal shear stress amplitude. By using the electrical potential drop method, Tanaka observed that the crack nucleation life was reduced with increasing stress concentration, on the other hand the crack propagation life increased. The experimental fatigue results, originally expressed in terms of nominal shear stress amplitud , have been reanalys d by means of the lo al strain en rgy densi y (SED) averag d over a control volume having radius R 0 surrounding he notch tip. To xclude all ex rinsic ffects actin ur ng the fatigue crack propagation phase, such as s iding con act and/or friction between fracture surfaces, crack initiation life has been c nsidered in the present work (*). In the original p per, initiation life was defined in correspondence of a 0.1÷0.4-mm-d ep crack. The co trol radius R 0 for f tigue strength ass ssment of notc ed components, thought of as a material property, has been estimated by imposing the constancy of the averaged SED for both smooth and cracked specimens at N A = 2 million loading cycles. (*) A version of the present contribution has already been presented at the 11 th International Conference on Multiaxial Fatigue and Fracture (ICMFF11). © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. 21st European Conference on Fracture, ECF21, 20-24 June 2016, Catania, Italy Synthesis of crack initiation life in steel notched specimens under torsional fatigue based on the averaged strain energy density Filippo Berto a,b , Alberto Campagnolo c , Giovanni Meneghetti c *, Keisuke Tanaka d a University of Padova, Departme t of Ma agement nd Engineering, Stradella S. Nicola 3, 36100, V cenza (Ital b NTNU, Department of Engineering Design and Materials, Richard Birkelands vei 2b, 749 , Trondheim, (Norway) c University f Padova, Department of Industri l Engineering, Via Venezia 1, 35131, Padova (Italy) d Meijo University, Department of Mechanical Engineering, 468-8502, Nagoya (Japan) Abstract Th torsional fatigue b haviour of circumferentially notched pecimens made of austenitic stainless steel, SUS316L, and carbon steel, SGV410, char cterized by differ nt notch roo radii has bee cently investig ted by Tanaka. I that contributi n, it was observed that the tot l fatigue life of the austenitic stainless steel incre ses with increasing stress concen r tion factor for a give applied nominal shear stress ampli ude. By using the electrical potential drop method, T n ka obs rved that the crack nucleation life was reduced w th increasing stress concentratio , on the other hand the crack propagation lif increased. The xperimental fatigu results, originally expressed in terms of nominal shear stres amplitud , have b e reanalysed by means of the local strain ener y ensity (SED) av raged ov r a control volume having radius R 0 surrounding the notch tip. To exclu e all extrinsic effects ac ing during t e fatigue crack propagation phase, su h as sliding contact a d/or friction betwe fracture urfac s, crack initiation life has been considered in the present work (*). In the original paper, i itia ion life was d fined in co respondence of a 0.1÷0.4-mm-deep crack. The control radius R 0 for fatigue str ngth ssessment f n tched components, thought of as material pr perty, has b en estimated by imposing the co stancy of the averaged SED for both smo th and cracked specimens at N A = 2 million loading cycles. (*) A version of the present contribution has already been presented at the 11 th International Conference on Multiaxial Fatigue and Fracture (ICMFF11). © 2016 The Autho s. Publ shed by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. 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.: 0039 049 8276751 E-mail address: giovanni.meneghetti@unipd.it * Correspon ing author. Tel.: 0039 049 8276751 E-mail address: giovanni.meneghetti@unipd.it

* Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt 2452 3216 © 2016 Th 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.2016.06.233