The influence of tip clearance on stall limits of a rectilinear cascade of compressor blades
Name
09162414.pdf
Size
4.07 MB
Format
Adobe PDF
Checksum (MD5)
1e095ba129d47bb2d69166b34ae8e25a
Author(s)
Khabbaz, Ghassan R. (Ghassan Raji)
Date Issued
1959
Publisher
Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1959]
Series/Report no.
GTL report #54
Abstract
An experimental study of the influence of tip clearance on the stall limits of compressor blades was conducted on a two dimensional rectilinear cascade. By using the mirror and image technique the end wall boundary layer in the gap was dispensed with. The clearance was found to relieve the pressure gradient and to retard stalling. The loading on the blade near the slot was found to be higher than that at a distance further along.
Description
August 1959
Also issued as: Thesis (M.S.)--Massachusetts Institute of Technology, Dept. of Mechanical Engineering, 1959
Includes bibliographical references (leaves 20-21)
Persistent DSpace Link
