Transition Modelling Implications in the CFD Analysis of a Turbine Nozzle Vane Cascade Tested Over a Range of Mach and Reynolds Numbers

Submitted by admin on Thu, 08/06/2015 - 10:58
TitleTransition Modelling Implications in the CFD Analysis of a Turbine Nozzle Vane Cascade Tested Over a Range of Mach and Reynolds Numbers
Publication TypeJournal Article
Year of Publication2015
AuthorsMarconcini M, Pacciani R, Arnone A
JournalJournal of Thermal Science
Volume24
Issue6
Pagination526-534
ISSN Number1003-2169
Accession NumberWOS:000364707400004
Other NumbersScopus 2-s2.0-84946397458
KeywordsCFD validation, Gas turbine, secondary flows, transition model
Abstract
The aerodynamic performance of a gas turbine nozzle vane cascade was investigated over a range of Mach and Reynolds numbers. The work is a part of a vast research project aimed at the analysis of fluid dynamics and heat transfer phenomena in cooled blades. In this paper computed results on the “solid vane” (without cooling devices) are presented and discussed in comparison with experimental data. Detailed measurements were provided by the University of Bergamo where the experimental campaign was carried out by means of a subsonic wind tunnel. The impact of boundary layer transition is investigated by using a novel laminar kinetic energy transport model and the widely used Langtry-Menter γ − Reθ,t model. 
The comparison between calculations and measurements is presented in terms of blade loading distributions, total pressure loss coefficient contours downstream of the cascade, and velocity/turbulence-intensity profiles within the boundary layer at selected blade surface locations at midspan. It will be shown how transitional calculations compare favorably with experiments.

 
URLhttp://link.springer.com/article/10.1007/s11630-015-0818-7
DOI10.1007/s11630-015-0818-7
Refereed DesignationRefereed