Research on the Flutter of Axial-Turbomachine Blading.
Abstract
The 'time marching' technique is successfully applied to the numerical computation of the nonstationary aerodynamics of a flat plate cascade for compressible flow of either subsonic or supersonic nature. The unsteady perturbation amplitudes of fluid properties are used as the dependent variables so that the computational domain can be reduced to a two-dimensional channel guided by two adjacent blades for any inter-blade phase angle. A new method of handling the boundary condition is developed with which the order of accuracy for the boundary points will be the same as for the interior points. The wake region behind the trailing edge of each blade in cascade is treated as a 'slip plane' as in two dimensional steady state supersonic flow. Results are in good agreement with existing solutions. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1974
- Accession Number
- AD0780467
Entities
People
- Fernando Sisto
- Ron Ho Ni
Organizations
- Stevens Institute of Technology