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LDA measurement of the passage flow field in an annular airfoil cascadeModels to predict the complex three-dimensional flow through turbomachine blade rows are being developed. To verify these models and direct necessary refinements, it is necessary that predictions be correlated with data obtained in experiments which model the fundamental three-dimensional blade row flow phenomena. This paper describes a series of experiments performed in a large scale, subsonic, annular cascade facility specifically designed to provide such data. In particular, the effect of incidence angle on the three-dimensional passage flow field through an annular cascade of cambered airfoils is investigated and quantified, accomplished by obtaining detailed and expensive LDA data. These data demonstrate and quantify the development of the passage vortices through the airfoil passage and their strong interaction with the endwall boundary layers.
Document ID
19880056691
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Stauter, R. C.
(Purdue Univ. West Lafayette, IN, United States)
Fleeter, S.
(Purdue University West Lafayette, IN, United States)
Date Acquired
August 13, 2013
Publication Date
January 1, 1987
Subject Category
Aerodynamics
Meeting Information
Meeting: International Symposium on Laser Anemometry,
Location: Boston, MA
Country: United States
Start Date: December 13, 1987
End Date: December 18, 1987
Accession Number
88A43918
Distribution Limits
Public
Copyright
Other

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