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Cold-air investigation of a 3 1/2-stage fan-drive turbine with a stage loading factor of 4 designed for an integral lift engine. 1: Turbine design and performance of first stageThe design of the 3 1/2-stage turbine is described, and the cold-air performance of the first stage, modified for axial inlet conditions, is presented. The performance of the modified single-stage turbine and of two comtemporary high-stage-loading-factor turbines is compared with that estimated with a reference prediction method.
Document ID
19750024984
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Whitney, W. J. (NASA Lewis Research Center Cleveland, OH, United States)
Schum, H. J. (NASA Lewis Research Center Cleveland, OH, United States)
Behning, F. P. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
October 1, 1975
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
E-8354
NASA-TM-X-3289
Report Number: E-8354
Report Number: NASA-TM-X-3289
Accession Number
75N33057
Funding Number(s)
PROJECT: RTOP 505-04
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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