가스터빈 동익 블레이드 회전이 팁 주변 열전달 계수에 미치는 영향에 대한 수치해석적 연구 = Rotational Effects of Gas Turbine Rotor Blade on Heat Transfer Coefficient Near the Tip Region

다국어 초록 (Multilingual Abstract)

In this study, the variations in heat transfer coefficients (HTC) on the turbine blade tip were compared for a stationary cascade configuration, a stationary cascade configuration with a moving shroud, and a 3D annular rotating blade with stationary nozzle. The tip HTC distributions of the stationary cascade cases and 3D rotor blade case were numerically investigated. It was revealed that the location and size of the hotspot HTC regions were different for each case. Furthermore, the HTC distributions of the 3D rotor blade were conducted for various relative motions. The results showed that at the lower relative motions, the HTC distribution is similar to that of the stationary cascade configuration. However, as the relative motion is increased, the hotspot location on the tip is moved toward the pressure side and trailing edge of the blade. It was observed that the dominant effect on the HTC pattern around the 3D rotor blade tip is the viscous force generated by the relative motion of the shroud and blade tip, which surpasses the effects of centrifugal and Coriolis forces on the heat transfer characteristics of the blade tip.
Additionally, the HTC distributions around the tip of the 3D rotor blade and the cascade configuration with a moving shroud were compared, which showed a similar overall HTC pattern. The findings of this study are anticipated to serve as valuable reference data for the implementation of cooling hole installations based on the hotspot regions on the gas turbine blade tips.