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Heat transfer and turbulence measurements of a film-cooled flow over a convexly curved surfaceHeat transfer and hydrodynamic boundary layer measurements were made in a turbulent boundary layer on a convex surface with 13 rows of injection. Both full- and partial-coverage cases were tested for three blowing ratios: 0.2, 0.4, and 0.6. Heat transfer results are discussed in terms of Stanton number with injection air temperature equal to wall temperature. In the blown region, for both m (blowing ratio) = 0.2 and 0.4, the local response of the boundary layer is dominated by curvature, and m = 0.4 shows higher cooling effects than m = 0.2 or 0.6, as expected, based on flat-plate results. Hydrodynamic measurements with a triple-hot-wire suggest the existence of two streamwise lanes. Lanes containing injection holes are highly affected by injection and show a definite streamwise evolution. Lanes which do not contain holes are not affected much by injection and show little change in the streamwise direction.
Document ID
19850059636
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Furuhama, K.
(Stanford Univ. CA, United States)
Moffat, R. J.
(Stanford University CA, United States)
Frota, M. N.
(Rio de Janeiro, Pontificia Universidade Catolica, Brazil)
Date Acquired
August 12, 2013
Publication Date
January 1, 1984
Subject Category
Fluid Mechanics And Heat Transfer
Meeting Information
Meeting: 1983 Tokyo International Gas Turbine Congress
Location: Tokyo
Country: Japan
Start Date: October 23, 1983
End Date: October 29, 1983
Accession Number
85A41787
Funding Number(s)
CONTRACT_GRANT: NAG3-3
Distribution Limits
Public
Copyright
Other

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