0
RESEARCH PAPERS: Gas Turbines: Structures and Dynamics

Determination of Blade Stresses Under Constant Speed and Transient Conditions With Nonlinear Damping

[+] Author and Article Information
J. S. Rao

Department of Mechanical Engineering, Indian Institute of Technology, New Delhi 110 016, India

N. S. Vyas

Department of Mechanical Engineering, Indian Institute of Technology, Kanpur 208 016, India

J. Eng. Gas Turbines Power 118(2), 424-433 (Apr 01, 1996) (10 pages) doi:10.1115/1.2816607 History: Received April 30, 1992; Online November 19, 2007

Abstract

Determination of resonant stresses is an important step in the life estimation of turbomachine blades. Resonance may occur either at a steady operating speed or under transient conditions of operation when the blade passes through a critical speed. Damping plays a significant role in limiting the amplitudes of vibration and stress values. The blade damping mechanism is very complex in nature, because of interfacial slip, material hysteresis, and gas dynamic damping occurring simultaneously. In this paper, a numerical technique to compute the stress response of a turbine blade with nonlinear damping characteristics, during steady and transient operations of the rotor, is presented. Damping is defined as a function of vibratory mode, rotor speed, and strain amplitude. The technique is illustrated by computing the stress levels at resonant rotor speeds for typical operation of a turbomachine.

Copyright © 1996 by The American Society of Mechanical Engineers
Your Session has timed out. Please sign back in to continue.

References

Figures

Tables

Errata

Discussions

Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In