Investigation of Rotating Stall in a Single-Stage Axial Compressor Page: 3 of 29
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2 NACA TN 5823
Experimental work has already been conducted on compressors, in
particular by Harvard University, the California Institute of Technology,
and the National Advisory Committee for Aeronautics (refs. 4to 6). How-
ever, in each instance the work has been carried out on multirow machines,
and it appears that considerable interference results from the downstream
Since the theories are in variance and the interference due to other
blade rows has an unknown effect, the present investigation has been con-
ducted on a single-stage machine, with and without downstream stator
blades, in an effort to verify the predicted results with a minimum of
interference; however, it was not found possible to remove the inlet
guide vanes. The data obtained permit a ready comparison between pre-
dicted and actual stall-propagation velocities and, in addition, allow
the theoretical models for the downstream flow field to be checked by
measurement of the pressure fluctuations.
This investigation was conducted at the Massachusetts Institute of
Technology under the sponsorship and with the financial assistance of
A effective blade passage area
A' total blade passage area
b half wave length of stall cell
c resultant velocity
Cp pressure coefficient
CX axial velocity
cy tangential velocity
f stall-propagation frequency
F frequency of timing pulse on photographs
L blade chord length
N number of stall cells
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Montgomery, S. R. & Braun, J. J. Investigation of Rotating Stall in a Single-Stage Axial Compressor, report, January 1957; (digital.library.unt.edu/ark:/67531/metadc56040/m1/3/: accessed January 24, 2019), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.