The Impact of Blade and Material Damping in Turbine Blades

I. Hamidipoor; N. Golsanamlou; I. Zare; P. Moradi

doi:doi:10.11648/j.ijsqa.20150103.14

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The Impact of Blade and Material Damping in Turbine Blades

I. Hamidipoor, N. Golsanamlou, I. Zare, P. Moradi

Published in International Journal of Science and Qualitative Analysis (Volume 1, Issue 3)

Received: 8 July 2015 Accepted: 28 August 2015 Published: 2 September 2015

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Abstract

A method of determining equivalent viscous damping ratio for different rotational speeds and modes as a function of displacement or strain at a reference point in a blade is presented. This method can be adopted using a suitable finite element code, e.g., ANSYS or ABAQUS. The friction damping concept is widely used to reduce resonance stresses in turbomachines. A friction damper has been designed for high pressure turbine stage of a turbojet engine. The objective of this work is to find out effectiveness of the damper while minimizing resonant stresses for sixth and ninth engine order excitation of first flexure mode. The capability to assess damping in the blade from finite element codes avoids costly tests at the initial stages of design.

Published in	International Journal of Science and Qualitative Analysis (Volume 1, Issue 3)
DOI	10.11648/j.ijsqa.20150103.14
Page(s)	64-68
Creative Commons	This is an Open Access article, distributed under the terms of the Creative Commons Attribution 4.0 International License (http://creativecommons.org/licenses/by/4.0/), which permits unrestricted use, distribution and reproduction in any medium or format, provided the original work is properly cited.
Copyright	Copyright © The Author(s), 2015. Published by Science Publishing Group

Keywords

Friction Damping, Turbine, Resonant Stress, Blade, Vibration, Friction Coefficient

References

[1]	J. S. Rao, Turbomachine Blade Vibration, Wiley, New York, 1991.
[2]	J. S. Rao, N. S. Vyas, K. Gupta, Blade damping measurement in a spin rig with nozzle passing excitation simulated by electromagnets, Shock & Vibration Bulletin 56 (pt 2) (1986) 109.
[3]	J. S. Rao, N. S. Vyas, Determination of blade stresses under constant speed and transient conditions with nonlinear damping, Journal of Engineering for Gas Turbines and Power, Transactions American Society of Mechanical Engineers 118 (2) (1996) 424.
[4]	F. E. Rowett, Elastic hysteresis in steel, Proceedings of the Royal Society 89 (1914).
[5]	E. P. Petrov and D. J. Ewins, “Advanced modeling of underplatform friction dampers for analysis of bladed disk vibration,” Journal of Turbomachinery, vol. 129, no. 1, pp. 143–150, 2007.
[6]	J. S. Rao, A.K. Singh, C.V. Ramakrishnan, K. Gupta, The effect of nonlinear damping on the resonant stresses in turbomachine LP rotor blades, I Mech. E. Vibrations in Rotating Machinery, Conference Transactions, 12–14 September 2000, Nottingham, UK, p. 45.
[7]	ANSYS workbench 14.0, ANSYS Inc., Canonsburg, PA.
[8]	C. M. Harris, C. E. Crede, Shock and Vibration Handbook, McGraw-Hill, New York, 1976.
[9]	Gui N, Fan JR, Cen KF, et al. A direct numerical simulation study of coherent oscillation effects of swirling flows. Fuel 2010; 89: 3926–3933.
[10]	C. W. Schwingshackl et al., “Measured and estimated friction interface parameters in a nonlinear dynamic analysis,” Mechanical Systems and Signal Processing, vol. 28, pp. 574–584, 2012.
[11]	J. Szwedowicz, C. Gibert, T. P. Sommer, and R. Kellerer, “Numerical and experimental damping assessment of a thin walled friction damper in the rotating setup with high pressure turbine blades,” Journal of Engineering for Gas Turbines and Power, vol. 130, no. 1, Article ID 012502, 2008.
[12]	R. K. Giridhar, P. V. Ramaiah, G. Krishnaiah, and S. G. Barad1, Gas Turbine Blade Damper Optimization Methodology, Advances in Acoustics and Vibration Volume 2012, Article ID 316761, 13 pages doi:10.1155/2012/316761.

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APA Style

I. Hamidipoor, N. Golsanamlou, I. Zare, P. Moradi. (2015). The Impact of Blade and Material Damping in Turbine Blades. International Journal of Science and Qualitative Analysis, 1(3), 64-68. https://doi.org/10.11648/j.ijsqa.20150103.14

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ACS Style

I. Hamidipoor; N. Golsanamlou; I. Zare; P. Moradi. The Impact of Blade and Material Damping in Turbine Blades. Int. J. Sci. Qual. Anal. 2015, 1(3), 64-68. doi: 10.11648/j.ijsqa.20150103.14

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AMA Style

I. Hamidipoor, N. Golsanamlou, I. Zare, P. Moradi. The Impact of Blade and Material Damping in Turbine Blades. Int J Sci Qual Anal. 2015;1(3):64-68. doi: 10.11648/j.ijsqa.20150103.14

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@article{10.11648/j.ijsqa.20150103.14,
  author = {I. Hamidipoor and N. Golsanamlou and I. Zare and P. Moradi},
  title = {The Impact of Blade and Material Damping in Turbine Blades},
  journal = {International Journal of Science and Qualitative Analysis},
  volume = {1},
  number = {3},
  pages = {64-68},
  doi = {10.11648/j.ijsqa.20150103.14},
  url = {https://doi.org/10.11648/j.ijsqa.20150103.14},
  eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.ijsqa.20150103.14},
  abstract = {A method of determining equivalent viscous damping ratio for different rotational speeds and modes as a function of displacement or strain at a reference point in a blade is presented. This method can be adopted using a suitable finite element code, e.g., ANSYS or ABAQUS. The friction damping concept is widely used to reduce resonance stresses in turbomachines. A friction damper has been designed for high pressure turbine stage of a turbojet engine. The objective of this work is to find out effectiveness of the damper while minimizing resonant stresses for sixth and ninth engine order excitation of first flexure mode. The capability to assess damping in the blade from finite element codes avoids costly tests at the initial stages of design.},
 year = {2015}
}

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TY  - JOUR
T1  - The Impact of Blade and Material Damping in Turbine Blades
AU  - I. Hamidipoor
AU  - N. Golsanamlou
AU  - I. Zare
AU  - P. Moradi
Y1  - 2015/09/02
PY  - 2015
N1  - https://doi.org/10.11648/j.ijsqa.20150103.14
DO  - 10.11648/j.ijsqa.20150103.14
T2  - International Journal of Science and Qualitative Analysis
JF  - International Journal of Science and Qualitative Analysis
JO  - International Journal of Science and Qualitative Analysis
SP  - 64
EP  - 68
PB  - Science Publishing Group
SN  - 2469-8164
UR  - https://doi.org/10.11648/j.ijsqa.20150103.14
AB  - A method of determining equivalent viscous damping ratio for different rotational speeds and modes as a function of displacement or strain at a reference point in a blade is presented. This method can be adopted using a suitable finite element code, e.g., ANSYS or ABAQUS. The friction damping concept is widely used to reduce resonance stresses in turbomachines. A friction damper has been designed for high pressure turbine stage of a turbojet engine. The objective of this work is to find out effectiveness of the damper while minimizing resonant stresses for sixth and ninth engine order excitation of first flexure mode. The capability to assess damping in the blade from finite element codes avoids costly tests at the initial stages of design.
VL  - 1
IS  - 3
ER  -

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Author Information

I. Hamidipoor

Department of Mechanical Engineering, Miami University, Ohio, USA
N. Golsanamlou

Department of Mechanical Engineering, Faculty of Engineering, Najafabad Branch, Islamic Azad University, Najafabad, Isfahan, Iran
I. Zare

Department of Cell and Molecular Biology, Semnan University, Semnan, Iran
P. Moradi

Department of Mechanical Engineering, Jahrom University, Jahrom, Iran

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Plain Text BibTeX RIS

APA Style

I. Hamidipoor, N. Golsanamlou, I. Zare, P. Moradi. (2015). The Impact of Blade and Material Damping in Turbine Blades. International Journal of Science and Qualitative Analysis, 1(3), 64-68. https://doi.org/10.11648/j.ijsqa.20150103.14

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ACS Style

I. Hamidipoor; N. Golsanamlou; I. Zare; P. Moradi. The Impact of Blade and Material Damping in Turbine Blades. Int. J. Sci. Qual. Anal. 2015, 1(3), 64-68. doi: 10.11648/j.ijsqa.20150103.14

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AMA Style

I. Hamidipoor, N. Golsanamlou, I. Zare, P. Moradi. The Impact of Blade and Material Damping in Turbine Blades. Int J Sci Qual Anal. 2015;1(3):64-68. doi: 10.11648/j.ijsqa.20150103.14

Copy | Download

@article{10.11648/j.ijsqa.20150103.14,
  author = {I. Hamidipoor and N. Golsanamlou and I. Zare and P. Moradi},
  title = {The Impact of Blade and Material Damping in Turbine Blades},
  journal = {International Journal of Science and Qualitative Analysis},
  volume = {1},
  number = {3},
  pages = {64-68},
  doi = {10.11648/j.ijsqa.20150103.14},
  url = {https://doi.org/10.11648/j.ijsqa.20150103.14},
  eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.ijsqa.20150103.14},
  abstract = {A method of determining equivalent viscous damping ratio for different rotational speeds and modes as a function of displacement or strain at a reference point in a blade is presented. This method can be adopted using a suitable finite element code, e.g., ANSYS or ABAQUS. The friction damping concept is widely used to reduce resonance stresses in turbomachines. A friction damper has been designed for high pressure turbine stage of a turbojet engine. The objective of this work is to find out effectiveness of the damper while minimizing resonant stresses for sixth and ninth engine order excitation of first flexure mode. The capability to assess damping in the blade from finite element codes avoids costly tests at the initial stages of design.},
 year = {2015}
}

Copy | Download

TY  - JOUR
T1  - The Impact of Blade and Material Damping in Turbine Blades
AU  - I. Hamidipoor
AU  - N. Golsanamlou
AU  - I. Zare
AU  - P. Moradi
Y1  - 2015/09/02
PY  - 2015
N1  - https://doi.org/10.11648/j.ijsqa.20150103.14
DO  - 10.11648/j.ijsqa.20150103.14
T2  - International Journal of Science and Qualitative Analysis
JF  - International Journal of Science and Qualitative Analysis
JO  - International Journal of Science and Qualitative Analysis
SP  - 64
EP  - 68
PB  - Science Publishing Group
SN  - 2469-8164
UR  - https://doi.org/10.11648/j.ijsqa.20150103.14
AB  - A method of determining equivalent viscous damping ratio for different rotational speeds and modes as a function of displacement or strain at a reference point in a blade is presented. This method can be adopted using a suitable finite element code, e.g., ANSYS or ABAQUS. The friction damping concept is widely used to reduce resonance stresses in turbomachines. A friction damper has been designed for high pressure turbine stage of a turbojet engine. The objective of this work is to find out effectiveness of the damper while minimizing resonant stresses for sixth and ninth engine order excitation of first flexure mode. The capability to assess damping in the blade from finite element codes avoids costly tests at the initial stages of design.
VL  - 1
IS  - 3
ER  -

Copy | Download