Aero-Thermal Performance Of A Rotor Blade Cascade With Film Cooling In Passage Endwall
Keywords
Aero-thermal performance; Blade cascade; Film cooling within passage; Gas turbine
Abstract
This paper describes the numerical investigations on the aerodynamic and thermal performance of a rotor blade cascade with multiple film cooling rows in the passage. First, the experimental data on an annular cascade with upstream film cooling was compared with the numerical results to validate the numerical method. The CFD simulations of the models with a row of film holes at four different locations on the hub endwall were performed respectively. The aerodynamic and thermal performance under the interaction of the secondary flow and endwall film cooling are analyzed based on the CFD predicted streamlines of mainstream flow and film injection, the contours of total pressure loss on the sections located in the passage and at the blade exit, the pitch-averaged film cooling effectiveness and film cooling effectiveness contours. The results show that film holes placed at low level of iso-Mach line tends to provide a better cooling with a smaller amount of coolant.
Publication Date
1-1-2018
Publication Title
Proceedings of the ASME Turbo Expo
Volume
5A-2018
Document Type
Article; Proceedings Paper
Personal Identifier
scopus
DOI Link
https://doi.org/10.1115/GT2018-76899
Copyright Status
Unknown
Socpus ID
85054064323 (Scopus)
Source API URL
https://api.elsevier.com/content/abstract/scopus_id/85054064323
STARS Citation
Fu, Jinglun; Hossain, Jahed; and Kapat, Jayanta, "Aero-Thermal Performance Of A Rotor Blade Cascade With Film Cooling In Passage Endwall" (2018). Scopus Export 2015-2019. 7994.
https://stars.library.ucf.edu/scopus2015/7994