UNSTEADY STALL OF AXIAL FLOW COMPRESSORS
Abstract
Experimental study of the separation of a laminar boundary layer from walls moving upstream and downstream in a steady flow using a shrouded rotating cylinder in a wind tunnel was continued. Boundary layer velocity profiles were obtained over approximately half the range of angular positions on the cylinder which appear to be necessary in order to define separation velocity profiles for upstream- and downstream-moving walls. An analysis for compatibility conditions governing the existence of rotating circulation disturbances on a single-stage axial-flow com pressor disk was continued. The very severe re strictions imposed on the results previously reported (radial perturbation velocity component assumed equal to zero, no radial variation in flow variables) were relaxed to the extent that only the assumption that the radial perturbation velocity component was assemed zero. Under this assumption and imposing the conditions that the disturbance flow be bounded with time and axial distance from the compressor disk, it was found that, as before, the only possible rotating circulation disturbance on the compressor disk is one rotating with the blades.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1963
- Accession Number
- AD0410391
Entities
People
- G. R. Ludwig
- W. G. Brady
Organizations
- Calspan