Dusting Hole Film Cooling Heat Transfer on a Transonic Turbine Blade Tip

Figure 3

(a) Details of A1 film-cooled blade. (b) Variations of inlet stagnation temperature and ratio of total pressure to static pressure within the mainstream flow and variation of surface temperature at one location along the camber line within the squealer recess during a typical blowdown test for the dataset 2020-06-26-2025-c21. (c) Variation of local surface heat flux with surface temperature during a typical transient test at one location along the camber line within the squealer recess for the dataset 2020-06-26-2025-c21.

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