Vibrations of a Compressor Blade with Slip at the Root.

Abstract

A simple discrete analytical model is developed to represent the vibration response behavior of a jet engine compressor or turbine blade, primarily in the fundamental mode, allowing for slip at the root. The analysis is compared with experiment, and agreement is found to be satisfactory, indicating that some of the phenomena involved can be modeled in a simple way. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1980
Accession Number
ADA086852

Entities

People

  • David I. G. Jones

Organizations

  • Wright Laboratory

Tags

Communities of Interest

  • Advanced Electronics
  • Air Platforms

DTIC Thesaurus Topics

  • Air Force
  • Compressor Blades
  • Differential Equations
  • Dynamic Response
  • Equations
  • Equations Of Motion
  • Frequency
  • Geometry
  • Impedance
  • Materials
  • Materials Laboratories
  • Measurement
  • Modal Analysis
  • Partial Differential Equations
  • Plastic Explosives
  • Resonant Frequency
  • Shape

Fields of Study

  • Engineering
  • Physics

Readers

  • Aerodynamics.
  • Combustion and Flow Dynamics.
  • Theoretical Analysis.