ON THE THEORY OF DISRUPTED FLUTTER OF A TURBO BLADE,
Abstract
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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 05, 1965
- Accession Number
- AD0615429
Entities
People
- V. A. Uspenskii
Organizations
- National Air and Space Intelligence Center