带有热障涂层的涡轮叶片前缘气热耦合数值研究

Numerical Investigation of Conjugate Heat Transfer on a Gas Turbine Blade with TBC-coated at Leading Edge

采用气热耦合的数值计算方法以及考虑转捩的湍流模型,对采用热障涂层技术的某型气冷涡轮叶片前缘传热进行了数值研究。结果表明,由于热障涂层的高绝热性,热障涂层一方面大幅提高叶片的抗氧化和抗热腐蚀的能力,另一方面配合高效的冷却技术,可以降低金属叶片的工作温度和叶片内的温度梯度。

Using the numerical computation method of conjugate heat transfer and transition turbulence model, heat transfer numerical investigation on the air-cooling turbine blade with thermal barrier coating at the leading edge is carried out. The results show that, because of the high heat-insulating property of thermal barrier coating, it is able to improve the ability of resistance to oxidation and hot corrosion in a large degree. With the combination of efficient cooling technologies, thermal barrier coating has the ability to reduce the working temperature and the temperature gradient within the blade wall for its good heat insulation performance.