PSI - Issue 2_B

ScienceDirect Available online at www.sciencedirect.com Available online at ww.sciencedire t.com S ienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Struc ural Integrity 2 (2016) 1109–1116 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2016) 000–000 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2016) 000–000 ScienceDirect Structural Integrity Procedia 00 (2016) 000–000 ScienceDirect Structural Integrity Procedia 00 (2016) 000–000 Available online at www.sciencedirect.com Science irect Structural Integrity Procedia 00 (2016) 000–000 Available onlin at www.scien edirect.com Science ire rity Procedia 00 (2016) 000– v il l li t .sci ir ct.c i ir t Str t r l I t rity Procedia 00 (2016) 000–000 21st European Conference on Fracture, ECF21, 20-24 J Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2016) 0 0–000 21st European Conference on Fracture, ECF21, 20-24 June 2016, Catania, Italy 21st European Conference on Fracture, ECF21, 20-24 June 2016, Catania, Italy 21st European Conference on Fracture, ECF21, 20-24 June 2016, Catania, Italy 21st European Conference on Fracture, ECF21, 20-24 June 2016, Catania, Italy 21, 20-24 2016, Catania, Italy , t i , It l 21st European Conference on Fracture, ECF21, 20-24 June 2016, Catania, Italy

www.elsevier.com/locate/procedia www.elsevier.com/locate/ procedia www.elsevier.com/locate/ procedia www.elsevier.com/locate/ procedia www.elsevier.com/locate/ procedia www.elsevier.com/locate/ procedia www.elsevier.com/locate/ procedia www.elsevier.com/l / www.els i r. /l t / procedia

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.2016.06.142 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. eer-review under responsibility of the Scientific Committee of ECF21 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 Els vier B.V. Peer-review under responsibility of the Scientific Committee of ECF21 2 P er review under r sponsibility of the Scientific Committee of ECF21 2452-3216 2016 he uthors. Published by lsevier . . eer-revie under esponsib lity of the cientific o ittee of 21 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. Stationary vibrations and fatigue failure of compressor disks of variable thickness Burago N.G. 1 , Nikitin A.D. 2, 3 , Nikitin I.S. 2,3* , Yushkovsky P.A. 3 1 Institute for Problems in Mechanics of RAS, Moscow, 119526, Russia 2 Institute for Computer Aided Design of RAS, Moscow, 123056, Russia 3 Moscow Aviation Institute, Moscow,125993, Russia ___________________________________________________________________________________________________________________ Abstract . The purpose of the research is calculating the stress-strain state of the elastic compressor disks of gas turbine engine due to vibrations of blades. The thickness of the disks is variable along the radius. The solution presented by Fourier series and the Fourier coefficients are found from the boundary value problems for systems of ordinary differential equations along the radial coordinate. The obtained results are used to estimate the durability of the disks in very-high-cycle fatigue mode. Key words: disk of variable thickness, stress-strain state, high frequency loading, very-high-cycle fatigue, durability estimation _________________________________________________________________________________________________________________________________ Nomenclature r ,  , z - polar coordinates ( ) h r - variable thickness of disk ij  - components of stress  - density r u ,  u , z u - components of displacement  ,  - Lame elastic moduli Stationary vibrations and fatigue failure of compressor disks of variable thickness Burago N.G. 1 , Nikitin A.D. 2, 3 , Nikitin I.S. 2,3* , Yushkovsky P.A. 3 1 fo Problems in Mechan cs , ow, 11952 , a 2 Institute for C mputer Aided Design of RAS, Moscow, 123056, Russia 3 Moscow Aviation Institute, Moscow,125993, Russia ___________________________________________________________________________________________________________________ Abstract . h purpose of the research is calculating the stress-strain state of the elastic compressor disks of gas turbine engine due to vibrations of blades. The thickness of the disks is variable along the radius. The solution presented by Fourier series and the Fourier coefficients are found from the boundary value problems for systems of ordinary differ ntial equations along the radial coordinate. The obtained results are used to estimate the durability of the disks in very-high-cycle fatigue mode. Key words: disk of variable thickness, stress-strain state, high frequency loading, very-high-cycle fatigue, durability estimation _________________________________________________________________________________________________________________________________ Nomenclature r ,  , z - polar co rdinates ( ) h r - variable thickness of disk ij  - components of stress  - density r u ,  u , z u - components of displacement  ,  - Lame elastic moduli Stationary vibrations and fatigue failure of compressor disks of variable thickness Burago N.G. 1 , Nikitin A.D. 2, 3 , Nikitin I.S. 2,3* , Yushkovsky P.A. 3 1 Institute for Problems in Mechanics of RAS, Moscow, 119526, Russia 2 Institute for Computer Aided Design of RAS, Moscow, 123056, Russia 3 Moscow Aviation Institute, Moscow,125993, Russia ___________________________________________________________________________________________________________________ Abstract . The purpose of the research is calculating the stress-strain state of the elastic compressor disks of gas turbine engine due to vibrations of blades. The thickness of the disks is variable along the radius. The solution presented by Fourier series and the Fourier coefficients are found from the boundary value problems for systems of ordinary differential equations along the radial coordinate. The obtained results are used to estimate the durability of the disks in very-high-cycle fatigue mode. Key words: disk of vari bl thickness, tre s-st ain state, high frequency loading, very-high-cycl fatigue, durability e timation _________________________________________________________________________________________________________________________________ Nomenclature r ,  , z - polar coordinates ( ) h r - variable thickness of disk ij  - comp ents of stress  - density r u ,  u , z u - components of displacement  ,  - Lame elastic moduli Stationary vibrations and fatigue failure of compressor disks of variable thickness Burago N.G. 1 , Nikitin A.D. 2, 3 , Nikitin I.S. ,3* , Yushkovsky P.A. 3 1 n t f r Problems in Mechan cs f A , M , 19526, ia 2 Institute for C mputer Aided Design of RAS, Moscow, 123056, Russia 3 Moscow Aviation Institute, Moscow,125993, Russia ___________________________________________________________________________________________________________________ Abstract . purpose of the research is calculating the stress-strain state of the lastic compressor disks of gas turbine engine du to vibratio s of blades. The thickness of the disks is variable along the radius. The solution presented by Fourier series and the Fourier coefficients are found from the bound ry value probl ms for ystems of ordinary differe tial quations along the radial coordinate. The obtained results are used to estimat the durability of the disk in very-high-cycle fatigue mode. Key words: disk of vari bl thickness, stress-strain state, high frequency loading, very-high-cycle fatigue, durability estimation _________________________________________________________________________________________________________________________________ Nomenclature r ,  , z - polar coordinates ( ) h r - variable t ickness of disk ij  - components of stress  - density r u ,  u , z u - components of displacement  ,  - Lame elastic moduli Stationary vibrations and fatigue failure of co pressor disks of variable thickness Burago N.G. 1 , Nikitin A.D. 2, 3 , Nikitin I.S. 2,3* , Yushkovsky P.A. 3 1 Institute for Problems in Mechanics of RAS, Moscow, 119526, Russia 2 Institute for Computer Aided Design of RAS, Moscow, 123056, Russia 3 Moscow Aviation Institute, Moscow,125993, Russia ___________________________________________________________________________________________________________________ Abstract . The purpose of the research is calculating the stress-strain state of the elastic compressor disks of gas turbine engine due to vibrations of blades. The thickness of the disks is variable alo g the radius. The solutio prese ted by Fouri r series and the Fourier coefficients are found from the boundary value problems for systems of ordinary differential eq ations along the radial coordinate. The obtained results are used to estimate the durability of the disks in very-hi h-cycle fatigue mode. Key words: disk of variable thickness, stress-strain state, high frequency loading, very-high-cycle fatigue, durability estimation _________________________________________________________________________________________________________________________________ Nomenclature r ,  , z - polar coordinates ( ) h r - variable thickness of disk ij  - compon nts of stress  - density r u ,  u , z - components of displacement  ,  - Lame elastic moduli Stationary vibrations and fatigue failure of co pressor dis of i k 1 3 _ _____ ______ ______ _____________________________________________________________ A rbine e gine d e to vibrations coef nts are fou d f n K _ omenclat ( ) h r - v able thickness of disk  s u , , components of isplacement L e St ti i ti f ti e fail i ks of variable thickness Burago N.G. 1 , Nikitin A.D. 2, 3 , Nikitin I.S. 2,3* , Yushkovsky P.A. 3 1 Institute for Proble s in echanics of RAS, Moscow, 119526, Russia 2 Institute for Computer Aided Design of S, osco , 123056, ussia 3 osco viation Institute, osco ,125993, ussia ___________________________________________________________________________________________________________________ A stract . he purpose of the research is calculating the stress-strain state of the elastic co pressor disks of gas turbine engine due to vibrations of blades. he thickness of the disks is variable along the radius. The solution presented by ourier series and the ourier coefficients are found fro the boundary value proble s for syste s of ordinary differential equations along the radial coordinate. he obtained results are used to esti ate the durability of the disks in very-high-cycle fatigue ode. Key words: disk of variable thickness, stress-strain state, high frequency loading, very-high-cycle fatigue, durability esti ation _________________________________________________________________________________________________________________________________ 21st European Conference on Fracture, ECF21, 20-24 June 2016, Catania, Italy Stationary vibrations and fatigue failure of compressor disks of variable thickn s Burago N.G. 1 , Nikitin A.D. 2, 3 , Nikitin I.S. 2,3* , Yushkovsky P.A. 3 1 Institute for Problems in Mechanics f RAS, Moscow, 119526, Russia 2 Institute for Computer Aided Design of RAS, Moscow, 123056, Russia 3 Moscow Aviation Institute, Moscow,125993, Russia ___________________________________________________________________________________________________________________ Abstract . The purpose of the research is calculating the stress-strain state of the elastic compressor disks of gas turbine engine due to vibrations of blades. The thickness of the disks i va iable along the radius. The solution present d by Fourier series and the Fourier coefficients are found from the boundary value problems for systems of ordinary differential equations along the radial coordinate. The obtained results are used to esti ate the durability of the disks in very-high-cycle fatigue mode. Key words: disk of variable thickness, stress-strain state, high frequency loading, very-high-cycle fatigue, durability estimation _________________________________________________________________________________________________________________________________ Nomenclature r ,  , z - polar c ordinates ( ) h r - variable thickness of disk ij  - components of stress  - density r u ,  u , z u - components of displacement  ,  - Lame elastic moduli C pyright © 2016 Th Auth rs. Published by Elsevier B.V. This is an open ccess rticle under the CC BY-NC-ND license (h tp://creativecomm ns.org/licen es/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. * Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt N 0 - number of blades on disk max  - maximum stress in cycle min  - minimum stress in cycle  - index of fatigue durability mean  - mean stress in cycle   - range of shear stress per cycle B  - ultimate tensile strength N 0 - number of blades on disk max  - maximum stress in cycle min  - minimum stress in cycle  - index of fatigue durability mean  - mean stress in cycle   - range of shear stress per cycle B  - ultimate tensile strength 2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21 N 0 - number of blades on disk max  - maximum stress in cycle min  - minimum stress in cycle  - index of fatigue durability ean  ean stress in cycle   - range of shear stress per cycle B  - ultim te ensile strength N 0 - number of blades on disk max  - maximum stress in cycle min  - minimum stress in cycle  - index of fatigue durability ean - mean stress in cycle   - range of shear stress per cycle B - ultimate tensile strength N 0 - number of blades on disk max - axi m str s i y l min  - mini u str ss in cycle  - index of fatigue durability mean  - mean stress in cycle   range of shear stress per cycle B  - ultimate tensile strength of torsion m  m str s tr n cycle ndex fatigue durability hear stress per c  Nomenclatur r ,  , z - lar c or i ates ( ) r - aria le t ic ess f is ij  - c e ts f stress  - density r ,  , z u - omponents of displacement  ,  - Lame elastic li ij - c e ts f strai - vibrat on frequency in l i s b - external radius of disk - section i t  - i te sity of torsion N 0 - number f blades o is ax  - a im m stress in c cle i  inimum tress in cycle - i e f fatig e ra ilit mean - ea stress i c cle   - ra e f s ear stress er c cle B - lti ate te sile strength ij  - components of strain  - vibration frequency a - i ternal radius of disk b - external radius of disk d section width  - intensity of torsion N 0 - number of blades on disk max  - maximum stress in cycle min  - minimum stress in cycle  - index of fatigue durability mean  - mean stress in cycle   - range of shear stress per cycle B  - ultimate tensile strength ij  - components of strain  - vibration frequency a - internal radius of disk b - external radius of disk d - section width  - intensity of torsion ij  - components of strain  - vibration frequency a - internal radius of disk b - external radius of disk d - section width  - intensity of torsion ij  - components of strain  - vibration frequency a - internal radius of disk b - external radius of disk d - section width  - intensity of torsion ij  - components of strain  - vibration frequency a - internal radius of disk b - xternal radius of disk d - section width  - intensity of torsion ij  - components of strain  - vibration frequency a - internal radius of disk b - ext r al radius of disk d section width  - intensity of torsion  - ponents o terna b ex l d - 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 ECF21