Publication:
Investigation of the effect of Reynolds number on laminar separation bubbles on controlled-diffusion compressor blades in cascade

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Authors
Schnorenberg, David G.
Subjects
Controlled-diffusion
Compressor
Stator
Cascade
Turbomachinery
Advisors
Hobson, Garth V.
Date of Issue
1996-06
Date
June 1996
Publisher
Monterey, California. Naval Postgraduate School
Language
en_US
Abstract
Detailed experimental investigation of second generation, controlled diffusion, compressor stator blades at an off-design inlet flow angle was performed in a low speed cascade wind tunnel using various experimental procedures. The objective of the study was the characterization of the off-design flow and the detailed investigation of flow separation which occurred near midchord. When it was found that the flow separation behavior was strongly influenced by the Reynolds number, the effect of Reynolds number variation on flow separation was investigated. Surface flow visualization was performed to gain general insight into the flow behavior. Blade surface pressure measurements were obtained using instrumented blades, from which coefficients of pressure were calculated. Laser Doppler velocimetry (LDV) was used to characterize the off-design flow upstream, in the passage between two blades, in the boundary layer on the suction side of the blades, and in the wake region. Overall, good comparisons between blade surface pressure measurements, LDV data and flow visualization were obtained for the separation region. At the highest Reynolds number, separation was turbulent and three dimensional and at the low Reynolds number the separation was predominately laminar and two dimensional.
Type
Thesis
Description
Series/Report No
Department
Department of Aeronautics and Astronautics
Other Units
Naval Postgraduate School
Identifiers
NPS Report Number
Sponsors
Funder
Format
126 p.
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.
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