Inlet Turbulence Distortion and Viscous Flow Development in a Controlled-Diffusion Compressor Cascade at Very High Incidence
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Authors
Hobson, G.V.
Shreeve, R.P.
Subjects
Advisors
Date of Issue
1993
Date
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Language
Abstract
Detailed two-component laser Doppler velocimeter (LDV) measurements of the flow through a controlled-diffusion
(CD) compressor cascade at a Reynolds number of about 700,000 and at a low Mach number are
reported in this article. A very high-incidence angle (8 deg above design) was considered throughout this
investigation, which included the full experimental characterization of the turbulence Held. The LDV measurements
were fully automated and were all taken in coincidence mode, thus turbulent flow correlations could
be determined. Most significant was the measurement of the distortion of the inlet freestream turbulence upstream
of the blade leading edges. Such information is important in assessing viscous codes which incorporate transport
equations to describe the turbulence within the flowfield. The laminar leading-edge separation bubble, which
reattached turbulent, was enlarged on the suction surface of the blade. Consistent with measurements at lower
incidence angles, the suction surface boundary layer remained attached over the rear part of the blade. The
pressure side boundary layer initially showed little or no growth, however, it finally developed into a profile
similar to a wall jet. The wake profiles showed significant asymmetry due to the high loading on the blades at
the increased incidence angle.
Type
Article
Description
The article of record as published may be found at http://dx.doi.org/10.2514/3.23635
Series/Report No
Department
Organization
Naval Postgraduate School (U.S.)
Identifiers
NPS Report Number
Sponsors
Naval Air Systems Command
Funder
Format
8 p.
Citation
Hobson, G. V., and R. P. Shreeve. "Inlet turbulence distortion and viscous flow development in a controlled-diffusion compressor cascade at very high incidence." Journal of Propulsion and Power 9.3 (1993): 397-404.
Distribution Statement
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.