A study of the end wall boundary layer in an axial compressor blade row
Name
14199856.pdf
Size
3.68 MB
Format
Adobe PDF
Checksum (MD5)
a3e60e673a987f34be6f7b52cff207cc
Author(s)
Moore, Raymond W. (Raymond William)
Richardson, David L.
Alternative Title
Shear flow in bends
Date Issued
1955
Publisher
Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1955]
Series/Report no.
GTL report #33
Abstract
Turbulent end wall boundary layers in the hub region of axial compressor blade rows have been studied in the Gas Turbine Laboratory. Both analytical and experimental work are presented. An attempt was made to predict the growth of the boundary layer momentum thickness as it passes through a cascade of blades using the momentum integral equation and several assumptions This calculation was compared with measurements taken along an assumed free streamline in a stationary cascade of blades supplied with an artificially skewed inlet boundary layer. From this comparison, the relative influence of individual terms in the momentum integral equation is deduced. The effects of inlet skewing and cross flow in the boundary layer in the region between blades is described. Two methods of representing main and cross flow velocity profiles are compared with experimental data.
Description
October 1955
Errata sheet inserted in front
At head of title: Shear flow in bends
Includes bibliographical references (page 12)
Persistent DSpace Link
