Numerical investigations of geometric design parameters defining nozzle guide vane endwall heat transfer
2006 (English)In: Proc. ASME Turbo Expo, 2006, 173-182 p.Conference paper (Refereed)
The objective of this work is to compare the predicted flow field and the endwall heat transfer of a baseline nozzle guide vane configuration with a combustion chamber variant, a heat shield variant without and with additional cooling air, and a cavity variant without and with additional cooling air. The comparison is carried out numerically using the commercial 3D Navier-Stokes software package Fluent . For the turbulence modeling the v2-f model by Durbin  been used. The detailed comparison of the flow field and the endwall heat transfer shows major differences between the baseline and heat shield configuration. The heat shield in front of the airfoil of the nozzle guide vane cascade influences the secondary flow field and the endwall heat transfer pattern strongly. The additional cooling air, released under the heat shield also has a distinctive influence. The cavity between the combustion chamber and the nozzle guide vane affects the secondary flow field and the endwall heat transfer pattern. Here the influence of the additional cavity cooling air is more decisive.
Place, publisher, year, edition, pages
2006. 173-182 p.
, Proceedings of the ASME Turbo Expo, 3 PART A
Endwall heat transfer, Heat transfer patterns, Secondary flow fields, Cascades (fluid mechanics), Computational geometry, Cooling systems, Heat shielding, Heat transfer, Parameter estimation, Turbulence, Vane pumps, Nozzles
Engineering and Technology
IdentifiersURN: urn:nbn:se:kth:diva-155968DOI: 10.1115/GT2006-90177ISI: 000242366800016ScopusID: 2-s2.0-33750883435ISBN: 079184238XISBN: 9780791842386OAI: oai:DiVA.org:kth-155968DiVA: diva2:766128
2006 ASME 51st Turbo Expo, 6-11 May 2006, Barcelona, Spain
QC 201411262014-11-262014-11-172014-11-26Bibliographically approved