Abstract
The effect of mainstream Mach number, including subsonic main flow at convergent section and supersonic main flow at divergent section of nozzle, on the film cooling effectiveness of cylindrical hole was studied in this paper. Two positions, which represent the different Mach number on the convergent-divergent nozzle, were chosen to arrange film hole at the convergent section and divergent section respectively. Pressure sensitive paint (PSP) technique was used to measure the film cooling effectiveness at five momentum ratios (0.05, 0.1, 0.15, 0.2 and 0.25). And numerical simulations were performed to analyse the related flow mechanism. The results showed that the increase of momentum ratio had slight effect on the film cooling effectiveness at low Mach number of mainstream in the convergent section. With the increase of the Mach number, the effect of momentum ratio on the film cooling effectiveness increases gradually. For the film hole at divergent section, although high momentum ratio led to secondary flow lift-off, the secondary flow lifting off was reattached to the wall and yielded wider spanwise coverage than that of convergent section.
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