Experimental and computational investigation of the endwall flow in a cascade of compressor blades
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Authors
Carlson, James R.
Subjects
laser Doppler velocimetry
controlled-diffusion compressor blading
controlled-diffusion compressor blading
Advisors
Hobson, Garth V.
Date of Issue
2000-09
Date
Publisher
Monterey, California. Naval Postgraduate School
Language
en_US
Abstract
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
Type
Thesis
Description
Series/Report No
Department
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NPS Report Number
Sponsors
Funder
Format
x, 112 p.;28 cm.
Citation
Distribution Statement
Approved for public release; distribution is unlimited.
Rights
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.