Slip Damping of Turbine Blades.

Abstract

An experimental, and an analytical, model of Turbine/Compressor blade with a circular root geometry is developed for the purpose of studying the effects of slip damping on the response of the blade. The expression for the energy dissipated by slip damping is presented. In addition the expressions for the energy dissipated by slip damping is presented. In addition the expressions for the energy dissipated by air and hysteresis damping are presented. The equation of motion for the blade is developed, and solved, to provide an expression relating the various parameters of the experimental and analytical models. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1978
Accession Number
ADA081907

Entities

People

  • Michael Charles Kimberling

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Advanced Electronics
  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Air Force
  • Blade Tips
  • Compressor Blades
  • Compressors
  • Engineering
  • Equations
  • Frequency
  • Geometry
  • Hysteresis
  • Mechanics
  • Modulus Of Elasticity
  • Radial Stress
  • Resonant Frequency
  • Shear Stresses
  • Strain Gages
  • Turbine Blades
  • Turbines

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Structural Dynamics.