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Research turbine for high temperature core engine application. 1: Cold-airoverall performance of solid scaled turbineA solid, half-scale model of a 50.8-cm (20-in) research turbine designed for a high temperature core engine application was investigated over a range of speeds and pressure ratios. The results of this test are presented. The effect of rotor blade twist was also investigated. At the design equivalent speed and specific work output, the total efficiency of the turbine with untwisted rotor blades was 87.1 percent; at the same pressure ratio the efficiency of the turbine with twisted rotor blades was 88.0 percent.
Document ID
19740008589
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Szanca, E. M. (NASA Lewis Research Center Cleveland, OH, United States)
Schum, H. J. (NASA Lewis Research Center Cleveland, OH, United States)
Hotz, G. M. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
February 1, 1974
Subject Category
Aerodynamics
Report/Patent Number
NASA-TN-D-7557
E-7592
Accession Number
74N16702
Funding Number(s)
PROJECT: RTOP 501-24
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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