by J. Szwedowicz, R. Visser, Walter Sextro, P. A. Masserey
Abstract:
Numerical predictions of the forced vibration of a disk assembly including frictional effects between the shrouds are presented concerning engineering needs for the blade design process. Assuming a tuned disk assembly, numerical static, free, and then forced vibration analyses of a shrouded turbine blade measured in the spin pit are performed systematically. For the excitation forces of an air jet evaluated from the fairly linear behavior of the experimental blade resonance peaks, the reliability of the proposed approach is validated through the very close agreement of the computed and measured resonant peaks. These resonant peaks demonstrate either a fairly linear behavior or a nonlinear one like the jump effect of blade resonance amplitudes, or elastic impacts between the shrouds. Also, the damping performance for different contact configurations between the shrouds is numerically analyzed. These numerical results indicate that the shrouds generate higher frictional damping for small angles (0â30deg) between the circumferential direction and the normal vector to the contact surface.
Reference:
Szwedowicz, J.; Visser, R.; Sextro, W.; Masserey, P. A.: On Nonlinear Forced Vibration of Shrouded Turbine Blades. Journal of Turbomachinery, volume 130, 2007. (10.1115/1.2218889)
Bibtex Entry:
@ARTICLE{Szwedowicz2007,
author = {Szwedowicz, J. and Visser, R. and Sextro, Walter and Masserey, P.
A.},
title = {On Nonlinear Forced Vibration of Shrouded Turbine Blades},
journal = {Journal of Turbomachinery},
year = {2007},
volume = {130},
pages = {011002--011002},
number = {1},
month = dec,
abstract = {Numerical predictions of the forced vibration of a disk assembly including
frictional effects between the shrouds are presented concerning engineering
needs for the blade design process. Assuming a tuned disk assembly,
numerical static, free, and then forced vibration analyses of a shrouded
turbine blade measured in the spin pit are performed systematically.
For the excitation forces of an air jet evaluated from the fairly
linear behavior of the experimental blade resonance peaks, the reliability
of the proposed approach is validated through the very close agreement
of the computed and measured resonant peaks. These resonant peaks
demonstrate either a fairly linear behavior or a nonlinear one like
the jump effect of blade resonance amplitudes, or elastic impacts
between the shrouds. Also, the damping performance for different
contact configurations between the shrouds is numerically analyzed.
These numerical results indicate that the shrouds generate higher
frictional damping for small angles (0{\^a}30deg) between the circumferential
direction and the normal vector to the contact surface.},
bdsk-url-1 = {http://dx.doi.org/10.1115/1.2218889},
comment = {10.1115/1.2218889},
issn = {0889-504X},
owner = {K. Agbons jr},
timestamp = {2013.11.23},
url = {http://dx.doi.org/10.1115/1.2218889}
}