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Effect of rotor tip clearance and configuration on overall performance of a 12.77-centimeter tip diameter axial-flow turbineThe rotor tip clearance was obtained by use of a recess in the casing above the rotor blades and also by use of a reduced blade height. For the recessed casing configuration, the optimum rotor blade height was found to be the one where the rotor tip diameter was equal to the stator tip diameter. The tip clearance loss associated with this optimum recessed casing configuration was less than that for the reduced blade height configuration.
Document ID
19790003844
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Haas, J. E. (Army Aviation Research and Development Command Cleveland, OH, United States)
Kofskey, M. G. (NASA Lewis Research Center)
Date Acquired
September 3, 2013
Publication Date
January 1, 1978
Subject Category
Aerodynamics
Report/Patent Number
AVRADCOM-TR-78-54
E-9181-1
NASA-TM-79025
Report Number: AVRADCOM-TR-78-54
Report Number: E-9181-1
Report Number: NASA-TM-79025
Meeting Information
Meeting: Ann. Intern. Conf.
Location: San Diego, CA
Country: United States
Start Date: March 11, 1979
End Date: March 15, 1979
Sponsors: Am. Soc. of Mech. Engr.
Accession Number
79N12015
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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