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Full potential solution of a transonic quasi-3-D flow through a cascade using artificial compressibilityA reliable method is presented for calculating the flowfield about a cascade of arbitrary 2-D airfoils. The method approximates the three-dimensional flow in a turbomachinery blade row by correcting for streamtube convergence and radius change in the throughflow direction. The method is a fully conservative solution of the full potential equation incorporating the finite volume technique on a body-fitted periodic mesh, with an artificial density imposed in the transonic region to ensure stability and the capture of shock waves. Comparison of results for several supercritical blades shows good agreement with their hodograph solutions. Other calculations for these profiles as well as standard NACA blade sections indicate that this is a useful scheme for analyzing both the design and off-design performance of turbomachinery blading.
Document ID
19810045575
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Farrell, C.
(NASA Lewis Research Center Cleveland, OH, United States)
Adamczyk, J.
(NASA Lewis Research Center Cleveland, Ohio, United States)
Date Acquired
August 11, 2013
Publication Date
March 1, 1981
Subject Category
Aerodynamics
Report/Patent Number
ASME PAPER 81-GT-70
Meeting Information
Meeting: Gas Turbine Conference and Products Show
Location: Houston, TX
Start Date: March 9, 1981
End Date: March 12, 1981
Sponsors: American Society of Mechanical Engineers
Accession Number
81A29979
Distribution Limits
Public
Copyright
Other

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