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Quasi-three-dimensional turbomachinery flow calculations on multiple hub-to-shroud stream surfacesResults are presented from a quasi-three-dimensional calculation of steady (relative), inviscid, adiabatic, subsonic/shock-free transonic flow on multiple hub-to-shroud stream surfaces through turbomachinery blade rows. The quasi-three-dimensional technique incorporates some three-dimensional effects while retaining much of the simplicity of two-dimensional computational methods. Three typical turbomachinery flowfield calculations are presented including an axial-flow compressor rotor, a turbine stator vane cascade, and a radial-inflow turbine rotor. The calculations were performed using quasi-three-dimensional extensions of existing two-dimensional methods. The current results represent an intermediate step in the complete quasi-three-dimensional solution process. However, the results demonstrate the usefulness of the quasi-three-dimensional technique in complementing and extending the applicability of the two-dimensional methods of turbomachinery flow analysis.
Document ID
19830057434
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Thompson, H. D.
(Purdue University West Lafayette, IN, United States)
Ragsdell, K. M.
(Arizona, University Tucson, AZ, United States)
Robinson, M. A.
(Purdue Univ. West Lafayette, IN, United States)
Date Acquired
August 11, 2013
Publication Date
July 1, 1983
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 83-1820
Accession Number
83A38652
Funding Number(s)
CONTRACT_GRANT: NSG-3105
Distribution Limits
Public
Copyright
Other

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