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Heat transfer in rotating passages with smooth walls and radial outward flowExperiments were conducted to determine the effects of rotation on heat transfer in turbine blade internal coolant passages. The experiments were conducted with a smooth wall, large-scale heat transfer model. The objective was to obtain the heat transfer data base required to develop heat transfer correlations and to assess computational fluid dynamic techniques for rotating coolant passages. An analysis of the governing equations showed that four parameters influence the heat transfer in rotating passages (coolant density ratio, Rossby number, Reynolds number, and radius ratio). These four parameters were varied over ranges that exceed the ranges of current open literature results, but that are typical of current and advanced gas turbine engine operating conditions. Rotation affected the heat transfer coefficients differently for different locations in the coolant passage. For example, heat transfer at some locations increased with rotation, but decreased and then increased again at other locations. Heat transfer coefficients varied by as much as a factor of five between the leading and trailing surfaces for the same test condition and streamwise location. Comparisons with previous results are presented.
Document ID
19910039036
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Wagner, J. H.
(United Technologies Research Center East Hartford, CT, United States)
Johnson, B. V.
(United Technologies Research Center East Hartford, CT, United States)
Hajek, T. J.
(Pratt and Whitney Group East Hartford, CT, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1991
Publication Information
Publication: ASME, Transactions, Journal of Turbomachinery
Volume: 113
ISSN: 0889-504X
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
ASME PAPER 89-GT-272
Accession Number
91A23659
Funding Number(s)
CONTRACT_GRANT: NAS3-23691
Distribution Limits
Public
Copyright
Other

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