Unsteady high turbulence effect on turbine blade film cooling heat transfer performance using a transient liquid crystal technique
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Experiments are conducted to study detailed distributions of heat transfer coefficients and film effectiveness for a gas turbine blade. Results indicate: Nusselt numbers increase with an increase in free-stream turbulence level, and also increase with the addition of unsteady wakes; the trailing edge ejection increases Nusselt numbers on the front parts of both the blade suction and pressure surfaces; film injection promotes earlier laminar to turbulent boundary layer transition on the suction surface and also greatly enhances local Nusselt numbers; unsteady wakes slightly enhance Nusselt numbers but significantly reduce film effectiveness on a film-cooled blade; and an increase in blowing ratio increases Nusselt numbers for both coolants.
author list (cited authors)
Du, H., Ekkad, S. V., & Han, J. C.
complete list of authors
Du, H||Ekkad, SV||Han, JC