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Radially-Graduated Turbine-Temperature ProfileProposed scheme to change temperature distribution in gas-turbine flame increases radially instead of remaining spatially uniform offers important advantages. Radially increasing temperature allows higher mean gas temperature, greater power output, higher rotational speed and longer life for blades. Principle suitable for axial-flow gas turbine directly in line with cylindrical combustor. Included in category many rocket, aircraft, stationary, and shipboard turbines.
Document ID
19830000607
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Tech Brief
Authors
Wagner, W. R. (Rockwell International Corp.)
Nitz, F. P. (Rockwell International Corp.)
Strangeland, M. L. (Rockwell International Corp.)
Date Acquired
August 11, 2013
Publication Date
November 1, 1984
Publication Information
Publication: NASA Tech Briefs
Volume: 8
Issue: 2
ISSN: 0145-319X
Subject Category
Mechanics
Report/Patent Number
MFS-19831
ISSN: 0145-319X
Report Number: MFS-19831
Accession Number
83B10607
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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