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contributor authorJacobi, Simon
contributor authorRosic, Budimir
date accessioned2019-02-28T11:09:36Z
date available2019-02-28T11:09:36Z
date copyright10/17/2017 12:00:00 AM
date issued2018
identifier issn0889-504X
identifier otherturbo_140_01_011002.pdf
identifier urihttp://yetl.yabesh.ir/yetl1/handle/yetl/4253306
description abstractThe integrated combustor vane concept for power generation gas turbines with can combustors has been shown to have significant benefits compared to conventional nozzle guide vanes (NGV). Aerodynamic loss, heat transfer levels, and cooling requirements are reduced while stage efficiency is improved by approximately 1.5% (for a no-swirl scenario). Engine realistic combustor flow with swirl, however, leads to increased turning nonuniformity downstream of the integrated vanes. This paper thus illustrates the altered integrated vane stage performance caused by inlet swirl. The study shows a distinct performance penalty for the integrated vane rotor as a result of increased rotor incidence and the rotor's interaction with the residual swirl core. The stage efficiency advantage of the integrated combustor vane concept compared to the conventional design is thus reduced to 0.7%. It is furthermore illustrated how integrated vane profiling is suitable to reduce the turning variation across the span downstream of the vane, further improve stage efficiency (in this case by 0.23%) and thus mitigate the distinct impact of inlet swirl on integrated vane stage performance.
publisherThe American Society of Mechanical Engineers (ASME)
titleInfluence of Combustor Flow With Swirl on Integrated Combustor Vane Concept Full-Stage Performance
typeJournal Paper
journal volume140
journal issue1
journal titleJournal of Turbomachinery
identifier doi10.1115/1.4037820
journal fristpage11002
journal lastpage011002-8
treeJournal of Turbomachinery:;2018:;volume 140:;issue 001
contenttypeFulltext


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