Heat transfer for a turbine blade with nonaxisymmetric endwall contouring

Stephen P. Lynch, Narayan Sundaram, Karen A. Thole, Atul Kohli, Christopher Lehane

Research output: Contribution to journalArticlepeer-review

80 Scopus citations


Complex vortical secondary flows that are present near the endwall of an axial gas turbine blade are responsible for high heat transfer rates and high aerodynamic losses. The application of nonaxisymmetric, three-dimensional contouring to the endwall surface has been shown to reduce the strength of the vortical flows and decrease total pressure losses when compared with a flat endwall. The reduction in secondary flow strength with nonaxisymmetric contouring might also be expected to reduce endwall heat transfer. In this study, measurements of endwall heat transfer were taken for a low-pressure turbine blade geometry with both flat and three-dimensional contoured endwalls. Endwall oil flow visualization indicated a reduction in the passage vortex strength for the contoured endwall geometry. Heat transfer levels were reduced by 20% in regions of high heat transfer with the contoured endwall, as compared with the flat endwall. The heat transfer benefit of the endwall contour was not affected by changes in the cascade Reynolds number.

Original languageEnglish (US)
Article number011019
JournalJournal of Turbomachinery
Issue number1
StatePublished - 2011

All Science Journal Classification (ASJC) codes

  • Mechanical Engineering


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