A computational study of the flow in a transonic axial compressor using an inviscid, three-dimensional finite difference
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06550488.pdf
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4.76 MB
Format
Adobe PDF
Checksum (MD5)
8289cb84bab46c632cf6600077be2a4e
Author(s)
Haymann-Haber, Guido
Date Issued
1979
Publisher
Cambridge, Mass. : Massachusetts Institute of Technology, Gas Turbine & Plasma Dynamics Laboratory, [1979]
Series/Report no.
GT & PDL report ; no. 145
Abstract
A computational study of the flow in a Transonic Axial Compressor has been performed. This compressor has a tip Mach number of 1.2 and an inlet hub to tip ratio of 0.5. The numerical procedure used is a fully three-dimensional, inviscid, finite difference algorithm. MacCormack's two-step, explicit second order accurate scheme was used. A total of 30,600 mesh points were used. The results were compared to space and time resolved exit flow measurements, and to quantitative density visualization pictures. Among the most significant features resolved by the computation, was an unusual shock structure, which had earlier been observed in the experiments. The general agreement of the computation with The experiment is good, except in regions dominated by viscous flow. Many of the effects of viscosity can be anticipated from the inviscid flow field.
Description
May 1979
Originally presented as the author's thesis, M.S., in the M.I.T. Dept. of Aeronautics and Astronautics, 1979
Includes bibliographical references (leaf 82)
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