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: 2 of 41
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NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS
INVESTIGATION OF A 10-STAGE SUBSONIC AXIAL-FLOW RESEARCH COMPRESSOR
III - INVESTIGATION OF ROTATING STALL, BLADE VIBRATION, AND SURGE
AT LOW AND INTERMEDIATE COMPRESSOR SPEEDS
By Merle C. Huppert, Eleanor L. Costilow, and Ray E. Budinger
An investigation of rotating stall and surge at low and intermedi-
ate speeds was conducted on a 10-stage subsonic axial-flow research
compressor. The fluctuations of rotating stall and surge were detected
by hot-wire anemometers and pressure transducers.
At 50 percent of design speed the flow fluctuations accompanying
rotating stall were found at all weight flows. The number of stall
regions in the stall pattern varied from three at the highest weight
flow investigated to seven near the surge point. At 60 percent of
design speed only the stall patterns with three and four stall regions
were obtained, and at 70 percent of design speed only the stall pattern
with three stall regions was found. For all stall patterns obtained,
the stall regions revolved about the compressor axis in the direction of
compressor rotation at about 57 percent of compressor speed.
The amplitude of the flow fluctuations of stall was greatest in the
first four stages and diminished somewhat in the latter stages. In the
first four stages the amplitude of the fluctuations was greatest at the
tip section and somewhat less at the hub section.
An analysis of the possibility of compressor blade vibration indi-
cated that only the inlet guide vanes and first stator were in danger of
fatigue failure from resonant vibrations excited by rotating stall. The
inlet guide vanes were the only blades to exhibit fatigue cracks during
the course of the investigation of this compressor.
The hot-wire anemometer and pressure transducer data obtained dur-
ing surge at 50 percent of design speed indicate that the surge pulse
was initiated by a general breakdown of flow in the compressor which
results in a rotating stall pattern with a single-stall region extending
from the compressor inlet to the compressor exit. At the minimum flow
rate during a surge pulse the stall region spread circumferentially to
cover the complete annulus of the compressor. The flow rate then
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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/m1/2/: accessed December 11, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.