The boundary layer on compressor cascade blades
Abstract
The characteristics of the flow field about highly loaded turbocompressor blades in a cascade wind tunnel were investigated. Experimental tests were conducted at chord Reynolds number (R sub c) near 500,000. A laser Doppler anemometer was employed in flow velocity measurement. Suction surface mean velocity and turbulence intensity profiles at a single incidence angle are presented. These data contribute to further understanding of two-dimensional boundary layer profiles, points of separation, and transition zones for turbomachine blades, and concomitantly, to compressor cascade predictive models.
- Publication:
-
Pennsylvania State Univ. Report
- Pub Date:
- May 1984
- Bibcode:
- 1984psu..reptQ....D
- Keywords:
-
- Axial Flow;
- Boundary Layer Flow;
- Compressor Blades;
- Flow Distribution;
- Flow Velocity;
- High Reynolds Number;
- Static Pressure;
- Turbomachine Blades;
- Turbulent Flow;
- Two Dimensional Boundary Layer;
- Axial Compression Loads;
- Boundary Layer Separation;
- Boundary Layer Transition;
- Cascade Wind Tunnels;
- Counterflow;
- Hot-Wire Anemometers;
- Laser Doppler Velocimeters;
- Leading Edges;
- Pressure Gradients;
- Suction;
- Turbomachinery;
- Fluid Mechanics and Heat Transfer