Effect of Sound Absorbing Wall Liners on Unsteady Aerodynamic Forces of a Cascade in a Supersonic Flow (1st Report, Vibrating Stators)

Masanobu Namba, Nobuhiko Yamasaki

Research output: Contribution to journalArticle

Abstract

A three-dimensional theory is developed for a linear cascade oscillating in a supersonic uniform flow between parallel walls to predict the effect of sound absorbing wall liners on the unsteady aerodynamic forces. A side wall of the model is partially composed of a sound absorbing liner with uniform acoustic admittance. The lined section of the wall is confined to the portion swept by blades. Substantial variation of the total aerodynamic work with change in the wall admittance is found to occur only in a confined effective range of the admittance magnitude. The effective range is located in a smaller admittance magnitude and the wall liner effect is larger and more complex for a supersonic cascade compared with a subsonic cascade. The effective range moves to the smaller admittance magnitude as the Mach number increases.

Original languageEnglish
Pages (from-to)2281-2288
Number of pages8
JournalTransactions of the Japan Society of Mechanical Engineers Series B
Volume53
Issue number492
DOIs
Publication statusPublished - Jan 1 1987

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unsteady aerodynamics
aerodynamic forces
supersonic flow
Supersonic flow
stators
linings
Stators
electrical impedance
Aerodynamics
cascades
Acoustic waves
Parallel flow
acoustics
Mach number
Acoustics
uniform flow
blades
aerodynamics

All Science Journal Classification (ASJC) codes

  • Condensed Matter Physics
  • Mechanical Engineering

Cite this

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abstract = "A three-dimensional theory is developed for a linear cascade oscillating in a supersonic uniform flow between parallel walls to predict the effect of sound absorbing wall liners on the unsteady aerodynamic forces. A side wall of the model is partially composed of a sound absorbing liner with uniform acoustic admittance. The lined section of the wall is confined to the portion swept by blades. Substantial variation of the total aerodynamic work with change in the wall admittance is found to occur only in a confined effective range of the admittance magnitude. The effective range is located in a smaller admittance magnitude and the wall liner effect is larger and more complex for a supersonic cascade compared with a subsonic cascade. The effective range moves to the smaller admittance magnitude as the Mach number increases.",
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