摘要
为了提高导向叶片的冷却效率,分析了层板导向叶片的外壁厚、冲击距离和扰流柱直径变化对叶片温度分布的影响,结果表明:随着冲击距离增加,冲击冷却效率降低,叶片表面温度升高;随着层板叶片外层壁厚度增大,外层壁两侧温差逐步增大;随着扰流柱直径增大,外层壁两侧平均温度呈现先降低后持平的变化趋势,两侧温差保持不变。结合中国铸造工艺设计了层板冷却涡轮导向叶片,利用CFX软件对设计的导向叶片流动传热进行计算,利用模拟试验对该导向叶片冷却效果进行验证。计算和试验结果表明:设计的层板冷却导向叶片冷却温降水平较高,温降均值达到燃气入口温度的40%以上,温降水平计算值比试验值低7.3%,叶片表面温度分布较均匀,叶片冷却结构设计合理。
In order to improve the cooling effectiveness of the turbine vane,the effect of laminated turbine vane outer wall thickness,impingement distance and pin-fins diameter on the turbine vane temperature distribution was analyzed. The results show that its impingement cooling efficiency decreases and its turbine vane outer wall temperature increases with the impingement distance increases. With the outer wall thickness of the laminate turbine turbine vane increases,the temperature difference on both sides of the outer wall gradually increases. With the increase of the pin-fins diameter,the average temperature on both sides of the outer wall decreases first and then flattens,and the temperature difference on both sides remains unchanged. The laminated cooling turbine vane was designed based on the casting process of China,the internal flow and temperature distribution of the turbine vane was calculated by CFX,the cooling efficiency of the turbine vane was validated by simulation test. The calculation and test results show that the laminated cooling turbine vane achieves a high temperature reduction,the average temperature reduction can achieve more than 40% of the inlet temperature of the gas. The calculated value of temperature reduction is 7.3% less than the test value. The temperature distribution on the turbine vane surface is symmetrical,the cooling structure is designed suitable.
作者
栾永先
沈跃
LUAN Yong-xian;SHEN Yue(AECC Shenyang Engine Research Institute,Shenyang 110015,China)
出处
《航空发动机》
北大核心
2021年第6期20-25,共6页
Aeroengine
基金
航空动力基础研究项目资助。
关键词
层板冷却
冲击距离
壁厚
扰流柱
导向叶片
航空发动机
laminated cooling
impingement distance
wall thickness
pin-fins
vane
aeroengine
