With the rapid increase of turbine inlet temperature and the application of pre-mixed combustion, turbine components, particularly the turbine endwall, works in extremely harsh environment and must be effectively cooled to ensure the component durability. Recently, new cooling schemes that employ both external film cooling and internal jet impingement cooling have drawn much attention due to their extraordinary performance. In this study, a numerical model of turbine endwall with jet impingement and film cooling was established and validated against the experimental results. To investigate the effects of geometric parameters related with this cooling scheme, five parameters including jet-to-target distance *L*~j~, impingement hole diameter *D*~i~, impingement hole-to-hole spacing *P*~i~, film hole diameter *D*~f~, film hole inclination angle *α* were selected to adjust upon the datum configuration. The Latin Hypercube sampling was used to collect a database that represented the design space formed by the five parameters. Performances including area averaged overall cooling effectiveness, maximum surface temperature gradient, average discharge coefficient of the system were evaluated through CFD calculation. To explore and exploit the design space as much as possible, a Kriging surrogate model was built from the database and updated by adding additional sample points. Analysis of variance (ANOVA) was conducted based upon the surrogate model to investigate the main effect of each parameter and the correlation between parameters. Finally, utilizing the knowledge obtained from ANOVA, improved designs were derived which yielded either better cooling performance or smaller coolant pressure drop within the system. Through detailed analysis of flow and heat transfer mechanisms of these improved designs along with the datum design, the influence of each parameter was illustrated clearly and suggestions for design of similar cooling scheme were drawn.


Effects of Cooling Configurations on the Aerothermal Performance of a Turbine Endwall With Jet Impingement and Film Cooling

Division / Sponsor:
International Gas Turbine Institute (IGTI)

Paper Proceedings: https://asmedigitalcollection.asme.org/GT/GT2020/volume/84058

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