A simple procedure to reduce secondary flow effect in turbine nozzle guide vanes

Bao Q. Nguyen, Kyle Squires

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

1 Scopus citations

Abstract

Secondary flow contributes about one-third of the total loss in turbine nozzle. Although secondary flow characteristics are well understood, it is still a challenge to mitigate the secondary flow effect. Several methods have been proposed to reduce secondary flow loss in turbine blade rows. They include: blade 3D stacking, blade 3D design, and end wall contouring, either axisymmetric and non-axisymmetric. The latter approach produces fully 3D end wall geometry, in contrast to the conventional axisymmetric shape. Several authors have applied elaborated procedure to adjust the end wall geometry of turbine blade rows. In this paper, we present a simple method to modify the hub wall of a turbine nozzle guide vane row with a single function. This function requires 2 geometry parameters which are established by CFD. The numerical results for a high work turbine nozzle guide vane show that a reduction in secondary kinetic energy is possible.

Original languageEnglish (US)
Title of host publicationProceedings of the ASME Turbo Expo 2007 - Power for Land, Sea, and Air
Pages905-915
Number of pages11
DOIs
StatePublished - Sep 25 2007
Event2007 ASME Turbo Expo - Montreal, Que., Canada
Duration: May 14 2007May 17 2007

Publication series

NameProceedings of the ASME Turbo Expo
Volume6 PART A

Other

Other2007 ASME Turbo Expo
CountryCanada
CityMontreal, Que.
Period5/14/075/17/07

ASJC Scopus subject areas

  • Engineering(all)

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    Nguyen, B. Q., & Squires, K. (2007). A simple procedure to reduce secondary flow effect in turbine nozzle guide vanes. In Proceedings of the ASME Turbo Expo 2007 - Power for Land, Sea, and Air (pp. 905-915). (Proceedings of the ASME Turbo Expo; Vol. 6 PART A). https://doi.org/10.1115/GT2007-28159