Title page for ETD etd-07282010-020119
|Type of Document
||Gauden, William H.
||Performance and stalling behavior of an axial-flow compressor subjected to three circumferential inlet distortion levels.
||Master of Science
|O'Brien, Walter F. Jr.
|Moses, Hal L.
|Thomas, William C.
|Date of Defense
The performance and stalling behavior of an axial-flow compressor
subjected to several different inlet distortion patterns was investigated.
The effect of inlet distortion on overall compressor performance
was determined through the measurement of compressor characteristics
for each inlet flow condition. Dynamic pressure transducers were employed
to investigate rotating stall cell behavior during the inception
of stall. Rotor blade response to distorted inflow was measured in the
form of average blade pressure profiles by using a scanning valve.
Results indicated a substantial reduction in total pressure rise
capability for distorted operation. A 25 per cent loss in stall
pressure rise was observed for the most severe distortion level. The
stall cell was found to rotate in the direction of rotor motion, but
at one-half the rotor speed. The cell encompassed the rotor blade
tip region down to approximately midspan. During the onset of stall,
the circumferential extent of the cell was observed to vary from 60 to
80 degrees. At the rotor blade tip the stall cell relative pressure
fluctuations indicated zero flow through the cell. The amplitude of
the stall cell was attenuated in the distorted flow region due to the
lower air velocity behind the distortion screens. Rotor blade suction
side pressure measurements indicated that increasing the circumferential
extent of distortion above some "critical" value induced blade stall
at higher flow rates. For the low speed compressor used, it appears
that the critical angle phenomena is a function of compressor design
and is independent of distortion level.
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