Unsteady Viscous Flow in a High Speed Core Compressor

Abstract

A probe incorporating a miniature high-frequency response pressure transducer has been traversed behind the first three stages of a high-speed multistage compressor operating at throttle settings corresponding to near choke, peak efficiency and near surge. A novel method of compensating for transducer temperature sensitivity was employed. Consequently, time-averaged pressures derived from the transducer were found to be in good agreement with pneumatic pressure measurements. Analysis of the unsteady pressure measurements revealed both the periodic and random fluctuations in the flowfield. This provided information on rotor-rotor interaction effects and the nature of viscous blade wake and secondary flows in each stage.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1990
Accession Number
ADA232989

Entities

People

  • J. D. Bryce
  • M. A. Cherrett

Organizations

  • Royal Aircraft Establishment

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Axial Flow
  • Axial Flow Compressors
  • Boundary Layer
  • Compressor Rotors
  • Data Acquisition
  • Flow
  • Fluid Flow
  • Frequency
  • Frequency Response
  • Layers
  • Mach Number
  • Measurement
  • Pressure Measurement
  • Procurement
  • Strain Gages
  • Unsteady Flow
  • Viscous Flow

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Fluid Dynamics.