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Considerations of turbine cooling systems for Mach 3 flightApproximate average midspan metal temperatures and coolant flow requirements for turbine airfoils cooled by compressor exit bleed air
Document ID
19680009718
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Stepka, F. S. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 2, 2013
Publication Date
April 1, 1968
Subject Category
Thermodynamics And Combustion
Report/Patent Number
NASA-TN-D-4491
Report Number: NASA-TN-D-4491
Accession Number
68N19187
Funding Number(s)
CONTRACT_GRANT: 720-03-51-05-22
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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