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Turbine for a low cost turbojet engine. 1: Design and cold-air performanceA 24.70-cm(9.72-in.) tip diameter single-stage, axial-flow turbine was designed for a turbojet engine. Cold-air tests were made over a range of speeds from 30 to 105 percent of design equivalent speed and over a range of total-pressure ratios from 1.30 to 2.66. Results are presented in terms of specific work, torque, mass flow, and efficiency.
Document ID
19740018139
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Kofskey, M. G. (NASA Lewis Research Center Cleveland, OH, United States)
Roelke, R. J. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
June 1, 1974
Subject Category
Propulsion Systems
Report/Patent Number
NASA-TN-D-7625
E-7754
Accession Number
74N26252
Funding Number(s)
PROJECT: RTOP 501-24
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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