Determination of the Subsonic Flutter Stability Boundary of Blade Rows at Large Angles of Attack

This paper presents an experimental-and-numerical method for determination of the subsonic flutter stability boundary of blade rows at large angles of incident flow. The aerodynamic test rig for determining the unsteady aerodynamic loads is described. The test results are presented for a straight ca...

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Bibliographic Details
Published in:Strength of materials 2018-03, Vol.50 (2), p.254-263
Main Authors: Kabannik, S. N., Zinkovskii, A. P., Stel’makh, A. L.
Format: Article
Language:English
Subjects:
Aerodynamic loads
Angle of attack
Characterization and Evaluation of Materials
Chemistry and Materials Science
Classical Mechanics
Flow stability
Gas turbines
Materials Science
Numerical methods
Solid Mechanics
Subsonic aircraft
Subsonic flutter
Vibration control
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Summary:This paper presents an experimental-and-numerical method for determination of the subsonic flutter stability boundary of blade rows at large angles of incident flow. The aerodynamic test rig for determining the unsteady aerodynamic loads is described. The test results are presented for a straight cascade of airfoils in a wide range of variation in the angle of attack and reduced vibration frequency, based on which the regularities in the effect of the angle of attack on the subsonic flutter stability boundary of blading are established.
ISSN:0039-2316
1573-9325
DOI:10.1007/s11223-018-9966-9