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Aerothermal performance of shielded vane design
Mälardalen University, School of Business, Society and Engineering, Future Energy Center. University of Oxford, Oxford, United Kingdom.ORCID iD: 0000-0002-2978-6217
University of Oxford, Oxford, United Kingdom.
2017 (English)In: Journal of turbomachinery, ISSN 0889-504X, E-ISSN 1528-8900, Vol. 139, no 11, 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
American Society of Mechanical Engineers (ASME) , 2017. Vol. 139, no 11, 111003
National Category
Energy Engineering
Identifiers
URN: urn:nbn:se:mdh:diva-36191DOI: 10.1115/1.4037126Scopus ID: 2-s2.0-85025165063OAI: oai:DiVA.org:mdh-36191DiVA: diva2:1130654
Available from: 2017-08-10 Created: 2017-08-10 Last updated: 2017-09-06Bibliographically approved

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