Accession Number:

AD0758721

Title:

Supersonic Torsional Flutter in Cascades.

Descriptive Note:

Final technical rept. 16 Feb 72-16 Feb 73,

Corporate Author:

PRATT AND WHITNEY AIRCRAFT EAST HARTFORD CONN

Personal Author(s):

Report Date:

1973-04-02

Pagination or Media Count:

58.0

Abstract:

A combined analytical and experimental study was made to determine the mechanism of supersonic unstalled torsional flutter in cascades of compressor blades. An unsteady supersonic cascade analysis was used to predict the onset conditions for supersonic torsional flutter. Two sets of blades, characteristic of those used in high-speed fan rotors, were tested to determine the position of the flutter boundary, and the characteristics of the aeroelastic instability. Author Modified Abstract

Subject Categories:

  • Fluid Mechanics
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE