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Cold-air performance of a 12.766-centimeter-tip-diameter axial-flow cooled turbine. 1: Design and performance of a solid blade configurationA solid blade version of a single-stage, axial-flow turbine was investigated to determine its performance over a range of speeds from 0 to 105 percent of equivalent design speed and over a range of total to static pressure ratios from 1.62 to 5.07. The results of this investigation will be used as a baseline for comparison with those obtained from a cooled version of this turbine.
Document ID
19750006648
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Haas, J. E. (NASA Lewis Research Center Cleveland, OH, United States)
Kofskey, M. G. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
January 1, 1975
Subject Category
Aerodynamics
Report/Patent Number
NASA-TN-D-7881
E-8124
Report Number: NASA-TN-D-7881
Report Number: E-8124
Accession Number
75N14720
Funding Number(s)
PROJECT: RTOP 505-04
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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