Experimental and computational investigation of the endwall flow in a cascade of compressor blades
By: James R. Carlson, II
Publisher: Naval Postgraduate School; Available from National Technical Information Service
Published: 2000
Place of publication: Monterey, Calif; Springfield, Va
Language: eng
Number of pages: 112
Description: An investigation of the three-dimensional flow in a cascade of second-generation controlled-diffusion blades, which was as a result of the interaction of the endwall boundary layers with the blade profiles, is reported. Five-hole probe wake surveys were performed at various spanwise locations to determine the total pressure loss distribution. Downstream velocity vector information was also obtained from the five-hole probe surveys. Two-component laser-Doppler velocimetry (LDV) was used to characterize the flow in the inlet and wake regions. A numerical investigation of the flowfield was conducted using SWIFT, a computational fluid dynamics code developed by Dr. Roderick Chima of NASA Glenn Research Center. Experimental blade-surface pressure coefficients were compared with values predicted using SWIFT. Overall, good correlation between the five-hole probe and LDV measurement techniques was obtained; however, the CFD predictions did not match well with the experimental results, particularly at the midspan location of the blade where separation of the suction surface boundary layer occurred.
Notes: Thesis advisor(s): Hobson, Garth V.

"September 2000."

Thesis (M.S. in Aeronautical Engineering) Naval Postgraduate School, September 2000.

Includes bibliographical references (p. 109)

"Approved for public release, distribution unlimited"--Cover.

Also available online.

Mode of access: World Wide Web.

System requirements: Adobe Acrobat reader.

US Navy (USN) author.

dk/dk cc:9116 1/4/01