Hotwire measurements of the turbulent flow into a cascade of controlled-diffusion compressor blades
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Authors
Wakefield, Bryce Edwin.
Subjects
Turbulence
Separation bubble
Hotwire
Free-shear layer
Cascade
Controlled-diffusion
Separation bubble
Hotwire
Free-shear layer
Cascade
Controlled-diffusion
Advisors
Hobson, Garth V.
Date of Issue
1993-12
Date
December 1993
Publisher
Monterey, California. Naval Postgraduate School
Language
en_US
Abstract
Turbulence measurements near the leading edge of a compressor stator were made in a subsonic cascade wind tunnel with a hotwire system. Using a single hot-film probe, velocity and turbulence distortion data were obtained about the leading edge of the Controlled-Diffusion (CD) blades in order to verify Laser Doppler Velocimetry (LDV) data taken in earlier studies. Measurements were conducted at a Mach number of .25, a Reynolds number of 711000 and an inlet flow angle of 48 degrees. Turbulence profiles obtained in the pitch-wise direction were found to be in good agreement with previous LDV measurements. These data indicated a localized increase in turbulence around the leading edge due to the interaction of the free-shear layer with the inlet turbulence. This free-shear layer extends over the separation bubble, which forms on the suction side of the blades' leading edge.
Type
Thesis
Description
Series/Report No
Department
Department of Aeronautics and Astronautics
Organization
Naval Postgraduate School (U.S.)
Identifiers
NPS Report Number
Sponsors
Funder
Format
55 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.