The paper presents an experimental study of heat/mass transfer coefficient in 1:4 rectangular channel with smooth or ribbed walls for Reynolds number in the range of 5000–40,000 and rotation numbers in the range of 0–0.12. Such passages are encountered close to the mid-chord sections of the turbine blade. Normal ribs and are placed on the leading and the trailing sides only. The experiments are conducted in a rotating two-pass coolant channel facility using the naphthalene sublimation technique. For purposes of comparison, selected measurements are also performed in a 1:1 cross section. The local mass-transfer data in the fully developed region is averaged to study the effect of the Reynolds and the rotation numbers. The spanwise mass transfer distributions in the smooth and the ribbed cases are also examined.
Heat Transfer in 1:4 Rectangular Passages With Rotation
Contributed by the International Gas Turbine Institute and presented at the International Gas Turbine and Aeroengine Congress and Exhibition, Atlanta, GA, June 16–19, 2003. Manuscript received by the IGTI December 2002; final revision March 2003. Paper No. 2003-GT-38615. Review Chair: H. R. Simmons.
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Agarwal , P., Acharya , S., and Nikitopoulos , D. E. (December 1, 2003). "Heat Transfer in 1:4 Rectangular Passages With Rotation ." ASME. J. Turbomach. October 2003; 125(4): 726–733. https://doi.org/10.1115/1.1626683
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