• 한국추진공학회지
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• 제16권2호
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• pp.42-50
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• 2012

열전달 연구의 목적은 온도와 열유속 분포를 보다 정확하게 예측하는 것이다. 이를 위해 상용 CFD 코드인 FLUENT를 사용하여 2종류의 노즐에 대해 질량유속비와 압력비를 계산하였으며, 실험결과와 잘 일치하였다. 또한 1종류의 노즐에 대해 FLUENT를 사용한 노즐 벽면에서의 열전달계수 계산결과는 노즐 축소부에서 실험결과 보다 약간 크게 예측되었으나 확대부에서는 잘 일치하고 있다. Bartz식을 이용한 열전달계수 계산결과는 전체적으로 실험결과 보다 크게 예측되었다. 계산결과가 실험결과와 차이를 보이는 원인은 노즐 내 급가속 유동에 의한 층류화, 난류모델 및 격자구성 등을 고려해 볼 수 있다.

• 대한기계학회논문집B
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• 제29권4호
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• pp.485-494
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• 2005

For the extensive investigation of local heat/mass transfer on the near-tip surface of turbine blade, experiments were conducted in a low speed stationary annular cascade. The turbine test section has a single stage composed of sixteen guide vanes and blades. The chord length and the height of the tested blade are 150 mm and about 125 mm, respectively. The blade has flat tip geometry and the mean tip clearance is about $2.5{\%}$ of the blade chord. Detailed mass transfer coefficient on the blade near-tip surface was obtained using a naphthalene sublimation technique. The inlet flow Reynolds number based on chord length and incoming flow velocity is changed from $1.0{\times}10^{5}\;to\;2.3{\times}10^{5}.$ Extremely complex heat transfer characteristics are observed on the blade surface due, to complicated flow patterns, such as flow acceleration, laminarization, transition, separation bubble and tip leakage flow. Especially, the suction side surface of the blade has higher heat/mass transfer coefficients and more complex distribution than the pressure side surface, which is related to the leakage flow. For all the tested Reynolds numbers, the heat/mass transfer characteristics on the turbine blade are the similar. The overall averaged $Sh_{c}$ values are proportional to $Re_{c}^{0.5}$ on the stagnation region and the laminar flow region such as the pressure side surface. However, since the flow is fully turbulent in the near-tip region, the heat/mass transfer coefficients are proportional to $Re_{c}^{0.8}.$