Title page for ETD etd-08012012-040031


Type of Document Master's Thesis
Author Ashby, George C.
URN etd-08012012-040031
Title Investigation of the effect of velocity diagram parameters on inlet total-pressure distortions through single-stage subsonic axial-flow compressors
Degree Master of Science
Department Aeronautical Engineering
Advisory Committee
Advisor Name Title
Pardue, Louis A. Committee Member
Whittemore, John A. Committee Member
Keywords
  • Compressors
Date of Defense 1957-05-15
Availability restricted
Abstract

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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