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Effect of the Combustor Wall on the Aerothermal Field of a Nozzle Guide Vane
Mälardalens högskola, Akademin för ekonomi, samhälle och teknik, Framtidens energi.
University of Oxford, United Kingdom.
2018 (engelsk)Inngår i: Journal of turbomachinery, ISSN 0889-504X, E-ISSN 1528-8900, Vol. 140, nr 5, artikkel-id 051010Artikkel i tidsskrift (Fagfellevurdert) Published
Abstract [en]

In gas turbines with can combustors the trailing edge of the combustor transition duct wall is found upstream of ev- ery second vane. This paper presents an experimental and numerical investigation of the effect of the combustor wall trailing edge on the aerothermal performance of the nozzle guide vane. In the measurements carried out in a high speed experimental facility, the wake of this wall is shown to in- crease the aerodynamic loss of the vane. On the other hand, the wall alters secondary flow structures and has a protective effect on the heat transfer in the leading edge-endwall junc- tion, a critical region for component life. The different clock- ing positions of the vane relative to the combustor wall are tested experimentally and are shown to alter the aerothermal field. The experimental methods and processing techniques adopted in this work are used to highlight the differences be- tween the different cases studied. 

sted, utgiver, år, opplag, sider
2018. Vol. 140, nr 5, artikkel-id 051010
HSV kategori
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URN: urn:nbn:se:mdh:diva-37506DOI: 10.1115/1.4038907ISI: 000430492900010Scopus ID: 2-s2.0-85046548519OAI: oai:DiVA.org:mdh-37506DiVA, id: diva2:1168058
Tilgjengelig fra: 2017-12-19 Laget: 2017-12-19 Sist oppdatert: 2018-05-24bibliografisk kontrollert

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