某型燃气轮机高压涡轮动叶冷却结构设计研究

Research on Cooling Structure Design of High Pressure Turbine Blade for Intercooled Gas Turbine

对某型燃气轮机高压涡轮动叶进行气热耦合数值模拟,分析了该叶片的温度场情况。叶片表面最高温度为1210 K左右,平均冷却效果为0.425。为了解决该叶片前缘温度较高且存在较大的温度梯度,以及顶部叶冠的冷却需要消耗大量冷却空气的问题,对该叶片进行了去掉顶部叶冠、增加前缘气膜的改型设计。通过对改型叶片进行数值模拟,并根据结果进行优化,最终得到一个满足设计要求的冷却结构。优化后的涡轮叶片前缘温度降到1150 K以下,平均冷却效果达到0.45,满足设计要求。

A numerical prediction was performed to study the temperature of high pressure turbine rotor blade.The maximum surface temperature of the blade surface is about 1 210 K,and the average cooling effect of the blade surface is 0.425.The blade leading edge has high temperature,and there is a large temperature gradient.While the cooling of the shroud requires a large amount of cooling air,the blade was modified to remove the shroud and increase the leading edge air film.By numerically simulating the modified blade and optimizing it based on the results generated,a cooling structure that can meet the design requirements is finally obtained.The optimized blade leading edge has temperature below 1 150 K,and the average cooling effect reaches 0.45,meeting the design requirements.