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Aerothermal Performance of Shielded Vane Design
Mälardalen University, School of Business, Society and Engineering, Future Energy Center. University of Oxford, United Kingdom.ORCID iD: 0000-0002-2978-6217
University of Oxford, United Kingdom.
2017 (English)In: Journal of turbomachinery, ISSN 0889-504X, E-ISSN 1528-8900, Vol. 139, no 11, article id 111003Article in journal (Refereed) Published
Abstract [en]

This paper presents an experimental investigation of the concept of using the combustor transition duct wall to shield the nozzle guide vane leading edge. The new vane is tested in a high-speed experimental facility, demonstrating the improved aerodynamic and thermal performance of the shielded vane. The new design is shown to have a lower average total pressure loss than the original vane, and the heat transfer on the vane surface is overall reduced. The peak heat transfer on the vane leading edge–endwall junction is moved further upstream, to a region that can be effectively cooled as shown in previously published numerical studies. Experimental results under engine-representative inlet conditions showed that the better performance of the shielded vane is maintained under a variety of inlet conditions.

Place, publisher, year, edition, pages
2017. Vol. 139, no 11, article id 111003
National Category
Fluid Mechanics and Acoustics
Identifiers
URN: urn:nbn:se:mdh:diva-37505DOI: 10.1115/1.4037126ISI: 000412232000003Scopus ID: 2-s2.0-85025165063OAI: oai:DiVA.org:mdh-37505DiVA, id: diva2:1168051
Available from: 2017-12-19 Created: 2017-12-19 Last updated: 2018-07-25Bibliographically approved

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Aslanidou, Ioanna

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