Aerodynamically Induced Vibration.

Abstract

An experimental investigation, performed in a large scale low-speed, single-stage compressor, was conducted to provide the radial and chordwise distribution of basic unsteady pressure data on the stator. Radial and circumferential distributions of streamwise and transverse velocity fluctuations were determined at stations upstream, inside and immediately downstream of the stator. Analysis of the results indicated a correlation of the normalized transverse fluctuation velocity component with stator incidence angle. The fluctuations were very large in the endwall regions and were attributed to poor flow conditions generated in the hub and tip endwall regions of the rotor.

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1981
Accession Number
ADA110493

Entities

People

  • James L. Bettner
  • Robert L. Jay

Organizations

  • General Motors

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Air Force
  • Base Lines
  • Blade Tips
  • Boundaries
  • Boundary Layer
  • Boundary Layer Flow
  • Data Acquisition
  • Dynamic Pressure
  • Experimental Data
  • Flow Fields
  • Flow Rate
  • Pressure Distribution
  • Pressure Measurement
  • Static Pressure
  • Steady State
  • Turbines
  • Vibration

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Atmospheric Science / Meteorology, specifically Wind Wave Turbulence.