Adiabatic effectiveness measurements in a first stage nozzle cascade having endwall contouring, leakage and assembly features

J. D. Piggush, Terrence W Simon

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

4 Scopus citations

Abstract

The first stage vane section of a modern gas turbine engine is assembled with a gap between the combustor and the vane platform and a second gap on the platform. To prevent ingression, leakage flow is provided through each gap. In this paper, the effectiveness of the leakage flow as an endwall film coolant is measured. The cascade geometry includes axial contouring of the cooled endwall and several step configurations for each gap. The steps reflect assembly or differential thermal growth misalignment. Various blowing rates are applied through each gap to allow assessment of the changes in effectiveness with changes in leakage rate. Thus, the results presented herein show how the gaps, steps, and leakage rates alter the cooling effectiveness of the leakage flow. Shown are some cases where steps improve the film cooling effectiveness. In other cases, enhanced mixing due to gaps, steps, or increased leakage reduces effectiveness.

Original languageEnglish (US)
Title of host publicationProceedings of the ASME Turbo Expo 2006 - Power for Land, Sea, and Air
Pages535-546
Number of pages12
Volume3 PART A
DOIs
StatePublished - Nov 15 2006
Event2006 ASME 51st Turbo Expo - Barcelona, Spain
Duration: May 6 2006May 11 2006

Other

Other2006 ASME 51st Turbo Expo
CountrySpain
CityBarcelona
Period5/6/065/11/06

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