Prediction of three-dimensional compressible turbulent boundary layers on transonic compressor blades
Name
915605847.pdf
Size
4.49 MB
Format
Adobe PDF
Checksum (MD5)
b626585f691fd1463da35ef29f111250
Author(s)
Usab, William J., Jr. (William James)
Date Issued
c1980
Publisher
c1980
Series/Report no.
GT & PDL report ; no. 152.
Abstract
A small crossflow approximation to the full three dimensional compressible turbulent boundary layer equations for turbomachine blade rows is developed by taking advantage of the nature of blade geometry and inviscid flow field when an intrinsic coordinate system is used. The resulting system of equations is solved by Keller's box scheme, providing the capability of numerically calculating compressible turbulent boundary layers on transonic compressor blades to a good approximation. The scheme is checked with two known solutions of incompressible flow over unloaded zero thickness blades. It is then applied to the first stage of a NASA Low-aspect-ratio rotor blade for which the inviscid flow field is available. The results give insight to the three-dimensional boundary layer character of transonic compressor blades, caused by an imbalance of centrifugal and Coriolis forces within the boundary layer.
Description
Includes bibliographical references
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