Abstract
Conjugate heat transfer simulations were conducted for the first stage rotor blade in an actual gas turbine and compared with experimental results. The objectives of this research are to validate prediction accuracy of temperature distribution on the rotor blade surface and find key factors to improve the prediction accuracy. These simulations were carried out at the similar condition as gas turbine operation. Temperature distributions predicted by the simulations reasonably agreed with those of the experiment near the rotor leading edge part. However, temperature distribution on the pressure side was different between the simulation and experiment. In the internal cooling flow passage, main stream leans toward one side of walls due to Coriolis force and the temperature on this side became lower than the experimental results. It is important for obtaining better prediction accuracy of heat transfer to solve the complex flow phenomena caused by several vortices generated by rotation, flow turning, or the rib-turbulator in the internal cooling flow region.
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