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A rapid blade-to-blade solution for use in turbomachinery designA rapid technique for solving the blade-to-blade turbomachinery flow problem was developed. Approximate governing flow equations, which include the effects of compressibility, radius change, rotation, and variable stream sheet thickness are solved using a panel method. The development and solution of these equations are described. Sample calculations are presented to illustrate the method's capabilities and accuracy. Previously announced in STAR as N83-13077
Document ID
19840048502
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Mcfarland, E. R. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 12, 2013
Publication Date
April 1, 1984
Publication Information
Publication: ASME, Transactions, Journal of Engineering for Gas Turbines and Power
Volume: 106
ISSN: 0022-0825
Subject Category
Aerodynamics
Report/Patent Number
ASME PAPER 83-GT-67
Accession Number
84A31289
Distribution Limits
Public
Copyright
Other

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