Investigation of secondary flow behavior and end wall boundary layer development through compressor cascades
Abstract
The three-dimensional performance of plane compressor cascades with colateral inlet wall boundary layers was investigated to formulate a viscous model to describe the flows. The fundamental phenomena influencing the flow field, particularly its viscous behavior, were studied along with the global performance, and end wall boundary layer with the blade passage. One fundamental result of the investigation shows that the passage vortex must be a result of inviscid flow phenomena, since it does not lead to significant additional loss. Another fundamental result is that the passage vortex primarily controls the spanwise distribution of the outlet flow angle. It is shown that secondary flow effects attributed to low aspect ratio blading are also observed at the aspect ratio when the inlet end wall boundary layer is sufficiently thick or main stream turning is large, and passage vortex is the mechanism which creates effectively low aspect ratio conditions by redistributing low energy boundary layer material. The global loss in total pressure for a cascade in three-dimensional flows is primarily dependent upon the actual behavior of the flow at midspan.
- Publication:
-
NASA STI/Recon Technical Report N
- Pub Date:
- June 1974
- Bibcode:
- 1974STIN...7522629S
- Keywords:
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- Boundary Layer Flow;
- Cascade Flow;
- Compressor Blades;
- Turbocompressors;
- Wall Flow;
- Aspect Ratio;
- Dynamic Models;
- Flow Distribution;
- Fluid Dynamics;
- Incompressible Flow;
- Secondary Flow;
- Vortices;
- Fluid Mechanics and Heat Transfer