ON THE THEORY OF DISRUPTED FLUTTER OF A TURBO BLADE

A theoretical solution is proposed for the problem of finding aerodynamic pressure forces acting against a unit of length of turbo-blade span, oscillating harmoniously. The solution results can be used to determine the critical rate of disruptive flutter and to determine deformations of blades with...

Full description

Saved in:
Bibliographic Details
Main Author: Uspenskii,V A
Format: Report
Language:English
Subjects:
AEROELASTICITY
ANGLE OF ATTACK
AXIAL FLOW COMPRESSORS
AXIAL FLOW TURBINES
FLUTTER
MATHEMATICAL ANALYSIS
OSCILLATION
SEPARATION
STABILITY
TURBINE BLADES
USSR
Online Access:Request full text
Tags: Add Tag
No Tags, Be the first to tag this record!
Description
Summary:A theoretical solution is proposed for the problem of finding aerodynamic pressure forces acting against a unit of length of turbo-blade span, oscillating harmoniously. The solution results can be used to determine the critical rate of disruptive flutter and to determine deformations of blades with subsequent finding of stresses in the sections along the length of the blade. Unedited rough draft trans. of Izvestiya Vysshikh Uchebnykh Zavedenii. Energetika (USSR) v7 n2 p68-73 1964. Available copy will not permit fully legible reproduction. Reproduction will be made if requested by users of DDC. Copy is available for public sale.