Aero-thermal investigation of a rib-roughened trailing edge channel with crossing-jets - Part II: heat transfer analysis

Alessandro Armellini, Filippo Coletti, Tony Arts, Christophe Scholtes

Research output: Chapter in Book/Report/Conference proceedingConference contribution

15 Scopus citations


The present contribution addresses the aero-thermal experimental and computational study of a trapezoidal cross-section model simulating a trailing edge cooling cavity with one rib-roughened wall and slots along two opposite walls. Highly resolved heat transfer distributions for the geometry with and without ribs are achieved using a steady state liquid crystals method in part 11 of this paper. The reference Reynolds number, defined at the entrance of the test section, is set at 67500for all the experiments. Comparisons are made with the flow field visualizations presented in part I of the paper. The results show the dramatic impact of the flow structures on the local and global heat transfer coefficients along the cavity walls. Of particular importance is the jet deflected by the rib-roughened wall and impinging on the opposite smooth wall. The experimental results are compared with the numerical predictions obtained using the finite volume, Reynolds-Averaged Navier-Stokes solver CEDRE.

Original languageEnglish (US)
Title of host publication2008 Proceedings of the ASME Turbo Expo
Subtitle of host publicationPower for Land, Sea, and Air
Number of pages11
EditionPART A
StatePublished - Dec 1 2008
Event2008 ASME Turbo Expo - 2008 ASME Turbo Expo, Germany
Duration: Jun 9 2008Jun 13 2008

Publication series

NameProceedings of the ASME Turbo Expo
NumberPART A


Other2008 ASME Turbo Expo
City2008 ASME Turbo Expo


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