In modern gas turbo-engines, the turbine blades are designed with various complex configurations of air cooling to reduce the blade temperature under running condition for safe operation.This paper deals with heat transfer in simulating turbine blade with rotating square and taper tubes. According to the experiment results, it is shown that the ratio of Nu (rotating state) to Nu. (non-rotating state) increases with rotating number Ro in the tailing edge, about 38% to 45% or so. But it is extremely complicated in the leading edge. As is shown in the Figs., the ratio of Nu to Nu. increases in the entrance region, decreases in some inner region, the lowest value reached to 18%.
