Heat transfer for a turbine blade with non-axisymmetric endwall contouring

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

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

15 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 non-axisymmetric, 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 to a flat endwall. The reduction of secondary flow strength with non-axisymmetric 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 percent in regions of high heat transfer with the contoured endwall, as compared to the flat endwall. The heat transfer benefit of the endwall contour was not affected by changes in the cascade Reynolds number.

Original languageEnglish (US)
Title of host publicationProceedings of the ASME Turbo Expo 2009
Subtitle of host publicationPower for Land, Sea and Air
Number of pages12
EditionPART B
StatePublished - 2009
Event2009 ASME Turbo Expo - Orlando, FL, United States
Duration: Jun 8 2009Jun 12 2009

Publication series

NameProceedings of the ASME Turbo Expo
NumberPART B


Other2009 ASME Turbo Expo
Country/TerritoryUnited States
CityOrlando, FL

All Science Journal Classification (ASJC) codes

  • General Engineering


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