A nonaxisymmetric endwall boundarylayer theory for axial compressor rows
Abstract
A second equation is deduced for the growth of the end wall boundary layer which connects the work of the mean blade force along the mean velocity with the energy of the secondary disturbances in the boundary layer. Secondary flow theory is used to obtain two equations for two boundary layer parameters. The method is regarded as an addition and modification to the Mellor and Wood treatment.
 Publication:

NASA STI/Recon Technical Report N
 Pub Date:
 1975
 Bibcode:
 1975STIN...7630495R
 Keywords:

 Boundary Layer Equations;
 Turbocompressors;
 Turbulent Flow;
 Wall Flow;
 Cascade Flow;
 Compressor Blades;
 Growth;
 Loads (Forces);
 Fluid Mechanics and Heat Transfer