TY - JOUR
T1 - Blade thickness effects on viscous flutter in a radial turbocharger turbine
AU - Sajedin, Azadeh
AU - Allport, John
AU - Amoozgar, Mohammadreza
AU - Marandi, Omid Farhangian
N1 - Publisher Copyright:
© 2022
PY - 2022/6/1
Y1 - 2022/6/1
N2 - Transient blade loading limits the lifetime of turbocharger turbine blades. This study investigates the flutter instability of a radial turbocharger turbine blade under pulsating inlet conditions. The viscous Navier-Stokes equations with the SST-kω turbulence model and curvature correction were solved. A time-marching 3D finite volume method was used in the CFX17 CFD solver to model the vibrating blade in a traveling wave mode applying Fourier Transformation. For flutter calculations, moving boundaries with specified modal displacements were used. An area of instability was recognized on the suction-side of the rotor blade. FSI steady-state analysis was then performed to assess the effects of shock position and blade profile on the blade stability in the recognized vulnerable region. The results show that a higher trailing edge radius increases the stability and leads to a significant reduction of flutter risk whereas the maximum thickness and leading-edge radius do not notably affect the flutter occurrences.
AB - Transient blade loading limits the lifetime of turbocharger turbine blades. This study investigates the flutter instability of a radial turbocharger turbine blade under pulsating inlet conditions. The viscous Navier-Stokes equations with the SST-kω turbulence model and curvature correction were solved. A time-marching 3D finite volume method was used in the CFX17 CFD solver to model the vibrating blade in a traveling wave mode applying Fourier Transformation. For flutter calculations, moving boundaries with specified modal displacements were used. An area of instability was recognized on the suction-side of the rotor blade. FSI steady-state analysis was then performed to assess the effects of shock position and blade profile on the blade stability in the recognized vulnerable region. The results show that a higher trailing edge radius increases the stability and leads to a significant reduction of flutter risk whereas the maximum thickness and leading-edge radius do not notably affect the flutter occurrences.
KW - Flutter
KW - Aeroelastic instability
KW - Fourier Transformation
KW - Turbocharger turbine
KW - Aerodynamic damping
UR - http://www.scopus.com/inward/record.url?scp=85126344692&partnerID=8YFLogxK
U2 - 10.1016/j.engfailanal.2022.106139
DO - 10.1016/j.engfailanal.2022.106139
M3 - Article
VL - 136
JO - Engineering Failure Analysis
JF - Engineering Failure Analysis
SN - 1350-6307
M1 - 106139
ER -
