【摘要】 为了给我国自主研发涡轮叶片提供理论基础，基于试验设计和响应面模型对某型叶片的冷却性能进行了数值研究。对某型涡轮叶片的设计参数进行了试验设计，数值研究了主流出口压力、主流进出口压比、冷气与主流温度比及流量比对叶片表面的无量纲温度分布的影响规律，并根据响应面模型拟合得到了叶片平均无量纲温度的经验公式。结果表明：根据试验设计和响应面模型拟合得到的叶片平均无量纲温度的经验公式有较高的精度；在设计参数范围内，涡轮叶片的平均无量纲温度随着主流出口压力(120～140 kPa)和冷气与主流温度比(0.6～0.7)的增大分别提高了0.57%和2.81%,随着主流进出口压比(1.3～1.5)和冷气与主流流量比(3～8)的增大分别降低了1.14%和3.68%。更多还原

【Abstract】 In order to provide a theoretical basis for China’s independent development of turbine blades, the cooling performance of a type of blade was numerically studied based on design of experiment and response surface model. The design parameters of a certain type of turbine blade were design of experiment, and the influence law of mainstream outlet pressure, pressure ratio of inlet and outlet, cold air to mainstream temperature ratio and flow rate ratio on blade surface dimensionless temperature distribution were studied numerically, and the empirical equation of blade average dimensionless temperature was obtained based on the fitting of response surface model. The results show that the empirical equation of the mean dimensionless temperature of the blade obtained according to the experimental design and response surface model fitting has high accuracy. In the range of design parameters, the average dimensionless temperature of turbine blades increases by 0.57% and 2.81% with the increase of mainstream outlet pressure(120-140 kPa) and cold air to mainstream temperature ratio(0.6-0.7), respectively. The average dimensionless temperature of the turbine blade decreases by 1.14% and 3.68% with the increase of mainstream pressure ratio of inlet and outlet(1.3-1.5) and cold air to main stream flow ratio(3-8), respectively.更多还原