Experimental technique and its validation for heat transfer in cooling channels at high rotation numbers

Based on analysis of cooling channel heat transfer theory and test system optimization, an experimental technology at high rotation numbers with gas pressure in cooling channel higher than 500 kPa was developed and implemented. The rotation number and Reynolds number ranged from 0 to 2.08 and 10⁴ to 7×10⁴, respectively, which covered the work parameters of real engine turbine blade. It is found that the effects of Reynolds number and rotation number on heat transfers in cooling channel are able to be separated. Under the condition of the same rotation number, the ratio of cooling channel heat loss and total heat and test error can be reduced to 18% and ±10% respectively in this scenario.