Title page for ETD etd-08012012-040031
|Type of Document
||Ashby, George C.
||Investigation of the effect of velocity diagram parameters on inlet total-pressure distortions through single-stage subsonic axial-flow compressors
||Master of Science
|Pardue, Louis A.
|Whittemore, John A.
|Date of Defense
A preliminary theoretical and experimental investigation of the
effect of velocity diagram parameters on inlet tota1—pressure distortions
through a single-stage subsonic axial-flow compressor for incompressible
flow has been conducted. The wake of l/4-inch—diameter rod, measured
both upstream and downstream of a rotor, has been compared for various
velocity diagrams. The measured downstream wake was also compared with
the downstream wake estimated by using a derived equation subject to the
assumption that (a) the undistorted and distorted flows enter the rotor
with the same absolute direction, (b) the static pressures of the undistorted and distorted
flows are equal at the inlet and also at the exit
of the rotor, (c) the increase of blade angle of attack in the distorted
flow is not sufficient to cause blade stall, and (d) the distorted flow
is turned in the rotor passage to the same exit direction, relative to the rotor, as the undistorted flow.>
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