An assessment of body force representations for compressor stall simulation
Name
639240558-MIT.pdf
Description
Full printable version
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7.47 MB
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Adobe PDF
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d62b41c3d4e850d30ecdac7e8ab522ef
Author(s)
Kerner, Jonathan (Jonathan H.)
Advisor(s)
Edward M. Greitzer and Choon S. Tan.
Date Issued
2010
Publisher
Massachusetts Institute of Technology
Abstract
This thesis examines an axial compressor body force representation constructed from 3D CFD calculations. The radial distribution of body forces is compared to that of a body force representation based on axisymmetric streamline curvature (SLC) calculations, and shown to be in qualitative agreement except in the vicinity of the blade tip. In terms of stall inception type and stall point, computations based on both representations exhibit agreement with rig test data. A parametric study is undertaken in which the magnitude of the forces in the blade tip region of both representations is reduced so as to obtain reductions in compressor pressure rise similar to those observed experimentally due to increased tip clearance. It is shown that on a back-to-back basis, a given change to the end wall forces produces similar effects on the computed stall point, whether the underlying body force representation derives from 3D CFD or SLC. Based on this result one route to capturing effects of tip clearance on stall prediction can be the development of a tip clearance body force model for use in conjunction with SLC calculations.
Description
Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2010.
Cataloged from PDF version of thesis.
Includes bibliographical references (p. 71-72).
Subjects
Aeronautics and Astronautics.
MIT Department
Massachusetts Institute of Technology. Department of Aeronautics and Astronautics
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