Viscous Flow in a Controlled Diffusion Compressor Cascade with Increasing Incidence
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Authors
Elazar, Y.
Shreeve, R.P.
Subjects
Advisors
Date of Issue
1989
Date
Publisher
ASME
Language
Abstract
A detailed two-component LDV mapping of the flow through a controlled diffusion compressor cascade at low Mach number (∼0.25) and Reynolds number of about 7×105, at three inlet air angles from design to near stall, is reported. It was found that the suction side boundary layer reattached turbulent after a laminar separation bubble, and remained attached to the trailing edge even at the highest incidence, at which losses were 3 to 4 times the minimum value for the geometry. Boundary layer thickness increased to fill 20% of the blade passage at the highest incidence. Results for pressure-side boundary layer and near wake are also summarized. Information sufficient to allow preliminary assessment of viscous codes is tabulated.
Type
Article
Description
Presented at the Gas Turbine and Aeroengine Congress and Exposition—June 4-8, 1989—Toronto, Ontario, Canada
Series/Report No
Department
Organization
Naval Postgraduate School (U.S.)
Identifiers
NPS Report Number
Sponsors
Naval Air Systems Command
NASA Lewis Research Center
NASA Lewis Research Center
Funder
Format
10 p.
Citation
Elazar, Y., and R. P. Shreeve. "Viscous flow in a controlled diffusion compressor cascade with increasing incidence." ASME 1989 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1989.
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.