Influence of Blade Tip Clearance on Aerodynamically Induced Vibration.

Abstract

An experimental investigation, whose objective was to demonstrate the influence of rotor blade tip clearance effects on the dynamic pressure induced on a downstream vane, was conducted in a large, low speed, single-stage research compressor. The blade tip clearance was 0.48% span. The rig was heavily instrumented with dynamic pressure gages on the vane hub, mean, and tip section suction and pressure surfaces. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1982
Accession Number
ADA123125

Entities

People

  • James L. Bettner

Organizations

  • General Motors

Tags

DTIC Thesaurus Topics

  • Acquisition
  • Aspect Ratio
  • Boundary Layer
  • Clearances
  • Compressor Rotors
  • Compressors
  • Data Acquisition
  • Dynamic Pressure
  • Flow Fields
  • Flow Visualization
  • Measurement
  • Pressure Distribution
  • Pressure Gages
  • Pressure Measurement
  • Standards
  • Steady State
  • Test Equipment

Fields of Study

  • Engineering
  • Physics

Readers

  • Aerodynamics.