PSI - Issue 14

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at www.sciencedire t.com ienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 14 (2019) 649–655 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

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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. © 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. 2nd International Conference on Structural Integrity and Exhibition 2018 Micro Structural Characterization of CF 8C Alloy and Its Effect on Tensile Properti s at Various Temperatures Neeta Paulose a *, Anuradha Nayak Majila a , Chandru Fernando D a , Parthasarathi Hans a a Materials Goup, Gas Turbine Research Establishment, C V Raman Nagar, Bangalore, 560093, India Abstract CF 8C alloy is an Iron-Chromium-Nickel austenitic stainless steel. It is a cast grade of AISI 347 stainless steel. CF 8C is niobium stabilized alloy and is extensively used in various components of Gas Turbine Engine and Turbocharger. It has good strength and ductility up to 550°C .Corrosion resistance is better than other austenitic stainless steel due to the presence of Niobium. Microstructure of this alloy consists of carbides and delta (δ) ferrite within austenitic matrix. The distribution, size and amount of delta ferrite are dependent on material processing condition. This paper is an attempt to understand the effect of delta ferrite on uniaxial tension testing at a constant strain rate over a range of temperatures. Detailed microstructral study and elemental analysis using optical and SEM has been carried out to understand delta (δ) ferrite distribution. © 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. Key word: Austenitic Stainless Steel; Gas Turbine Engine; Casting; CF 8C; δ ferrite; Tensile Test 1. Introduction The need for improved high strength, oxidation resistant, crack resistant cast stainless steel alloys for diesel, gasoline and gas-turbine engines led to the invention of CF 8C alloy. CF 8C is an iron-chromium-nickel-niobium alloy especially useful for field welding or for service involving long exposure to elevated temperature. Niobium helps to prevent grain boundary precipitation of chromium carbide when the material is heated in range 427-872oC thus making the alloy better corrosion resistant than other austenitic stainless steel. CF 8C are known to have three phases; gamma (ϒ) austenitic matrix with small amounts of delta (δ) ferrite (5-20%) and carbide M(C, N). J.P.Shingledecker et al. (2006) reported that the solidification temperature range for CF 8C alloy is 1450–1290°C. 2nd International Conference on Structural Integrity and Exhibition 2018 Micro Structural Characterization of CF 8C Alloy and Its Effect on Tensile Properties at Various Temperatures Neeta Paulose a *, An radha Nayak Majila a , Chandru Fernando D a , Parthas rathi Hans a a Materials Goup, Gas Turbine Research Establishment, C V Raman Nagar, Bangalore, 560093, India Abstract CF 8C alloy is an Iron-Chromium-Nickel austeniti stainless teel. It is a cast grade of AISI 347 stainl ss steel. CF 8C is iobium stabilized alloy and is extensively us d in various components of Gas Turbine Engin and Turbocharger. It ha good strength and du tility up to 550°C .Corr sion resistance is bett r than other auste itic stainless steel due to the presence of Ni bium. Microst ucture of this all y consists of carbides and del a (δ) ferrite within usten tic matrix. The distribution, ize and amount f delta ferrite are d pe dent on material processing condition. This aper is an attempt to understand the effect of d lta ferrite on niaxial ensio testing at a co stant strain rate ov r a range of temp atures. Deta led microstructral study and elemental analysis using optical and SEM has been carried out to understand delta (δ) ferrite distribution. © 2018 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND lic nse (https://creat vecommons.org/licenses/by- c-nd/4.0/) Selection and peer-review under responsibility of Peer-review under responsibility of the SICE 2018 organizers. Key word: Austenitic Stainless Steel; Gas Turbine Engine; Casting; CF 8C; δ ferrite; Tensile Test 1. Introduction The ne d for improved high strength, oxidation resistant, crack resistant ca t stainless steel alloys for diesel, gasoline and gas-turbine engines led to the invention of CF 8C alloy. CF 8C is an iron-chromium-nickel-ni i alloy especially useful for field w lding or f r service involving long exposure to elevated temperature. Niobium helps to prevent grain oundary precipitation of chromium carbide when the mat rial is heated i ra ge 427-872oC thus making the alloy better corrosion resistant than other austenitic stainless ste l. CF 8C are known to have three phases; amma (ϒ) austenitic matrix with small amounts of delta (δ) ferrite (5-20%) and carbide M(C, N). J.P.Shingledecker et al. (2006) reported that the solidification temperature range for CF 8C alloy is 1450–1290°C. © 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.: + 91 80 25040342, Mobile No.: 9341635258 E-mail address: neeta_paulose@gtre.drdo.in * Corresponding author: Tel.: + 91 80 25040342, Mobile No.: 9341635258 E-mail address: neeta_paulose@gtre.drdo.in

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 a open access article und r the CC BY-NC-ND lic nse (https://creat vecommons.org/licenses/by- c-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

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.2019.05.080