Heat transfer measurements in a first stage nozzle cascade having endwall contouring, leakage and assembly features

J. D. Piggush, T. W. Simon

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

18 Scopus citations

Abstract

This work supports new gas turbine designs for improved performance by evaluating sealing flow effects in a cascade representative of a contoured first stage stator passage. Contouring accelerates the flow, reducing the thickness of the endwall inlet boundary layer to the turbine stage and reducing the strength of secondary flows within the passage. Injected flows, used to seal gaps and cool surfaces, may affect endwall boundary layers, increase secondary flows and possibly create additional vortex structures in the passage. The present paper documents injected flow effects on the endwall heat transfer within a passage with one contoured and one straight endwall. The paper discusses heat transfer distributions measured with different leakage flow rates. In particular, leakage is from the gap between the combustor and turbine sections and from the gap at the assembly joint on the vane platform between two vanes.

Original languageEnglish (US)
Title of host publicationProceedings of the ASME Summer Heat Transfer Conference, HT 2005
Pages85-94
Number of pages10
DOIs
StatePublished - Dec 1 2005
Event2005 ASME Summer Heat Transfer Conference, HT 2005 - San Francisco, CA, United States
Duration: Jul 17 2005Jul 22 2005

Publication series

NameProceedings of the ASME Summer Heat Transfer Conference
Volume3

Other

Other2005 ASME Summer Heat Transfer Conference, HT 2005
CountryUnited States
CitySan Francisco, CA
Period7/17/057/22/05

Keywords

  • Contouring
  • Endwall
  • Film cooling
  • Heat transfer
  • Leakage
  • Nozzle
  • Secondary flows
  • Turbine vane

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