Title page for ETD etd-05092009-040547
|Type of Document
||James, Ralph William
||The effect of boundary layer blowing in the corner region of a linear compressor cascade wind tunnel
||Master of Science
|O'Brien, Walter F. Jr.
|Dancey, Clinton L.
|Date of Defense
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 coef'ficient 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.
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