The paper gives the results of investigation of the inlet flow irregularity influence on the film cooling formation. It is shown that the total pressure diagram irregularity in the set of nozzles inlet changes the structure of the film cooling in the initial region of the nozzle vane pressure side. Cooler flow displacement is registered in the regions of the total pressure gradient, interference of the perforation rows is broken, and overheat regions appear.
Film Cooling Forming Features of the Turbine Nozzle Vanes Leading Edge Neighborhood Taking into Account Entry Flow Irregularity
Russ. Aeronaut.
Russian Aeronautics ; 66 , 2 ; 308-315
01.04.2023
8 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Leading-Edge Injection for Film Cooling of Turbine Vanes
AIAA | 1977
|Conjugate Calculation of Gas Turbine Vanes Cooled with Leading Edge Films
British Library Online Contents | 2009
|