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Cold-air investigation of first stage of 4-1/2-stage, fan drive turbine with average stage-loading factor of 4.66The design procedure and the development of the blading geometry for the 4 and 1/2 stage turbine are discussed. Results obtained with the first stage, operated as a single stage turbine, are presented. A free vortex design meets the design requirements without incurring problems such as excessive turning, negative reaction, or high Mach number. Cold air tests of the single stage turbine showed that the turbine developed design work (stage loading factor of 5.26) at an efficiency of 0.86, which was the efficiency predicted by a reference method. The mass flow at this condition was 0.88, which occurred at design speed and a pressure ratio of 1.407, corresponding to a stage loading factor of 4.35. The efficiency at this condition was 0.003 higher than that predicted by the reference method.
Document ID
19810007535
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Whitney, W. J. (NASA Lewis Research Center Cleveland, OH, United States)
Moffitt, T. P. (NASA Lewis Research Center Cleveland, OH, United States)
Behning, F. P. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 4, 2013
Publication Date
January 1, 1981
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA-TP-1780
E-461
Accession Number
81N16050
Funding Number(s)
PROJECT: RTOP 505-32
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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