A study of the hub boundary layer in an axial flow compressor.

The annulus wall boundary leyer regions in an axial flow compressor have long been recognised as a major source of loss. The problem has been accentuated with the advent of the general acceptance of axial flow compressors for gas turbine applications. These units are being required to operate over an increasingly wide range· of operating conditions. For these requirements to be included in new designs, a clearer basic understanding of the flow in the associated loss regions would appear essential. In this thesis the hub boundary layer of a single stage axial flow compressor is examined with the view to formulating improved design rules for this region.