The mean coefficients of heat transfer from gas to turbine nozzle blade at high Reynolds numbers

The mean heat transfer in the flow section of a high-temperature gas turbine at high Reynolds number between six and seven million was examined. The experimental nozzle cascade is described and experimental velocity curves for assessing the aerodynamic efficiency of the blade profile are shown. The heat-transfer investigation involved calorimetric measurement with forward and reverse directions of the heat flux. The flow rate and temperature difference of water passing through the blade were measured, and the mean coefficients of heat transfer over the profile surface were calculated in the form of the ratio of heat flux density to the difference between the mean temperature of the surface and the inlet cascade flow temperature. The experimental results were used to derive a relation which is analyzed.