Investigation of a 10-stage subsonic axial-flow research compressor 3: investigation of rotating stall, blade vibration and surge at low and intermediate compressor speeds Page: 4 of 41
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NACA RM E53019
third, fourth, fifth, seventh, and tenth stages at 50, 60, and 70 per-
cent of design speed. The flow fluctuations of surge were measured at
50 percent of design speed with pressure transducers and hot-wire
The following symbols are used -tn this report:
A, CjE refer to radial stations (see table I)
fb natural bending frequency of compressor blade
(fb)n natural bending frequency at any rotor speed
(fb)st natural bending frequency at stationary conditions
fS frequency with which stall regions pass anemometer probe
h rotational speed of stall regions, rps
N compressor rotational speed, rps
P stagnation pressure, lb/sq in.
r ratio of local radius to tip radius
V velocity, ft/sec
w weight flow, b/sec
X time increment on oscillogram between appearance of stall at
one anemometer station and appearance of stall on other
z axial distance, in.
Mangle between two anemometer probes
8 ratio of stagnation pressure at compressor inlet PO to
standard pressure of 14.7 lb/sq in.
APc compressor pressure rise at surge point
APS change in stagnation pressure during surge
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Huppert, Merle C.; Costilow, Eleanor L. & Budinger, Ray E. Investigation of a 10-stage subsonic axial-flow research compressor 3: investigation of rotating stall, blade vibration and surge at low and intermediate compressor speeds, report, May 18, 1953; (digital.library.unt.edu/ark:/67531/metadc59783/m1/4/: accessed January 22, 2019), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.