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Examination of flow around second-generation controlled diffusion compressor blades in cascade at stall

Approved for public release, distribution is unlimited / The flow around second-generation controlled-diffusion blades in cascade at stall was examined experimentally through the use of a two-component laser-Doppler velocimeter. Blade surface pressure measurements were also preformed at mid span on the blades at various Reynolds numbers. Flow visualization techniques were used to observe and record the flow on the surface of the blade. A correlation between the experimental results and computational fluid dynamic predictions was attempted in order to determine the exact nature of the flow as the blades approached stall, to further assist in the development of advanced blade design. The blade surface pressure measurements showed that the mid-span section of the blade was at a lower loading than previously measured at a smaller inlet flow angle. This indicated that the blade section was at stall. The flow visualization highlighted the extent of the three-dimensional flow over the blades. The LDV measurements documented the mid-span boundary layer and wake profiles. / Ensign, United States Navy

Identiferoai:union.ndltd.org:nps.edu/oai:calhoun.nps.edu:10945/1589
Date06 1900
CreatorsFitzgerald, Kevin D.
ContributorsHobson, Garth V., Shreeve, Raymond P., Department of Mechanical and Astronautical Engineering
PublisherMonterey California. Naval Postgraduate School
Source SetsNaval Postgraduate School
Detected LanguageEnglish
TypeThesis
Formatx, 65 p. : ill. (some col.), application/pdf
RightsThis publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. As such, it is in the public domain, and under the provisions of Title 17, United States Code, Section 105, may not be copyrighted.

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