A method for three-dimensional flow analysis in a rotor using a high speed digital computer

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Authors
Felt, Donald L.
Subjects
Advisors
Vavra, M. H.
Date of Issue
1963
Date
1963
Publisher
Monterey, California: Naval Postgraduate School
Language
en_US
Abstract
Theoretical analyses of flow with rotating passages of turbi0machinery have become necessary for the proper design of turbo-pump elements in liquid fuel boosters and power conversion units. One such theory is presented, and a numerical solution derived. this theory develops a method for the analysis of steady, inviscid, adiabatic flow through arbitrary rotors. A detailed analysis in a meridional plane is given, assuming axial symmetry. A simplified approach to the blade to blade solution is also presented. The merits of these theories are compared with other proposed methods. The inverse, or design, approach is considered, and found to be unnecessary. A numerical solution for incompressible flow is derived and applied to the flow solution in the impeller of a mixed flow compressor with backwards-bent blades of arbitrary shape. Meridional streamlines and relative vorticity distributioins are progressively calculated on a CDC 1604 computer, using FORTRAN program language. Data are measured from a detailed presentation of the blade shape in a meridional plane. Blade to blade relative velocity distributions are calculated from the meridional plane analysis. It is concluded that the results completely define the flow and are sufficiently accurate for engineering applications. Validation is based upon the reliability of the theory, and upon comparisons with results of other methods. Extensions of the scope of this approach are recommended, which include the compressible solution and the solution of flows in unbladed passages.
Type
Thesis
Description
Series/Report No
Department
Aeronautical Engineering
Organization
Naval Postgraduate School (U.S.)
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Distribution Statement
Approved for public release; distribution is unlimited.
Rights
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.
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