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Analytic investigation of effect of end-wall contouring on stator performanceCalculations show improved stator performance when the tip end wall was contoured so that the inlet area was greater than the exit area. Comparisons are made with previously published experimental data. The results of a parametric analysis of the effect contour geometry on the efficiency of a highly loaded axial stator are given. The maximum stator efficiency gain is about 0.8 percentage point, and this represents a 22 percent reduction in stator losses. The degree to which endwall contouring reduces the forces driving secondary flows was also examined. The driving forces for both cross channel and radial secondary flow were reduced.
Document ID
19820006178
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Boyle, R. J.
(NASA Lewis Research Center Cleveland, OH, United States)
Rholik, H. E.
(NASA Lewis Research Center Cleveland, OH, United States)
Goldman, L. J.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 4, 2013
Publication Date
November 1, 1981
Subject Category
Aerodynamics
Report/Patent Number
NASA-TP-1943
E-719
Report Number: NASA-TP-1943
Report Number: E-719
Accession Number
82N14051
Funding Number(s)
PROJECT: RTOP 505-32-2B
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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