The effect of boundary layer blowing in the corner region of a linear compressor cascade wind tunnel

A fundamental investigation of the flow in the endwall corner region of a linear compressor cascade wind tunnel and the effect of boundary layer blowing in this region was conducted using blade surface pressure tap measurements and five - hole prism probe measurements taken downstream of the cascade. The results are presented as a series of velocity vector plots, loss contour plots, and pitchwise mass - averaged loss coefficient plots. The angle of attack test range was from 5 to 29 degrees. For the corner region boundary layer blowing investigations, two slots were machined into the ends of a set of cascade blades, and an external air source was used as the blade slot jet air source. Tests were done for 19, 21, and 23 degrees angle of attack. The main effect of corner boundary layer blowing was a significant reduction in total pressure losses in the region along the blade span between the exterior portion of the corner boundary layer flow and the blade profile boundary layer flow.

Name thesis:degree_name

Master of Science

Level thesis:degree_level

masters

Discipline thesis:degree_discipline

Mechanical Engineering

Department dc:contributor.department

Mechanical Engineering

Grantor dc:publisher

Virginia Tech

Year dc:date.issued

1995

Author dc:creator

• James, Ralph William

Chair dc:contributor.committeechair

• O'Brien, Walter F. Jr.

Committee members dc:contributor.committeemember

• Dancey, Clinton L.
• Moore, John

• wind tunnels

Statement dc:rights

• In Copyright

Licence dc:rights.uri

• http://rightsstatements.org/vocab/InC/1.0/

Language dc:language.iso

en

Dc Identifier Other

etd-05092009-040547

OAI identifier oai:identifier

oai:vtechworks.lib.vt.edu:10919/42554