Shock wave end wall boundary layer interaction in a transonic compressor rotor

The passage shock wave end wall boundary layer interaction in a transonic compressor was investigated with a laser transit anemometer. A two stage transonic compressor designed without inlet guide vanes was used in this flow field investigation. Measurements of the flow velocity were made within the first stage rotor passage of this transonic compressor. Laser measurements were made in two blade passages at six axial locations from 10% of the axial blade chord in front of the leading edge to 30% of the axial blade chord into the blade passage. At three of these axial locations, laser traverses were taken at different radial immersions to investigate the flow behavior near the tip end wall. Twenty-six different locations were traversed circumferentially. The measurements reveal that the end wall boundary layer in this region is separated from the core flow by what appears to be a shear layer where the passage shock wave and all ordered flow seem to end abruptly.

Name thesis:degree_name

Ph. D.

Level thesis:degree_level

doctoral

Discipline thesis:degree_discipline

Mechanical Engineering

Department dc:contributor.department

Mechanical Engineering

Grantor dc:publisher

Virginia Polytechnic Institute and State University

Year dc:date.issued

1987

Author dc:creator

• Rabe, Douglas Cameron

Chair dc:contributor.committeechair

• O'Brien, Walter F. Jr.

Committee members dc:contributor.committeemember

• Moses, Hal L.
• Pierce, F. J.
• Wood, Henry L.
• Ostdiek, F. R.

Statement dc:rights

• In Copyright

Licence dc:rights.uri

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

Handle dc:identifier.uri

http://hdl.handle.net/10919/49872

OAI identifier oai:identifier

oai:vtechworks.lib.vt.edu:10919/49872