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针对高压涡轮导向器叶片表面温度过高的情况,采用在叶片内安装导流片并布置射流孔的方式对高温叶片进行冲击冷却,运用带转捩的Transition k-kl-ω模型完成了气动和传热的三维耦合计算分析,研究了改善冲击冷却效果的方法和途径,实现在保持冷却气体流量不变条件下,提高冷却效果、降低材料的性能要求。计算结果表明:在一定孔径范围内,射流孔数和孔径满足(4n-1)D=h的关系式时,沿叶高方向能满足冷却要求;选择在压力面开3列、吸力面开4列射流孔,能满足叶片中弦区域冷却要求,采用劈缝排气方式可以消除尾缘高温现象;导流片与叶片间距zn/D在1.71～2.57变化时,对叶片内外表面平均温度影响不大,而随间距变小,叶片内外表面最高温度降低,最低温度则会升高;随冷却气体温度降低或流量增加,冷却效果会更好。
In view of the high surface temperature of the blade of the high-pressure turbine guider, the high-temperature blades are impingement-cooled by installing the guide vanes and arranging the jet holes in the vanes. The transition k-kl- Heat transfer analysis of the three-dimensional coupling, the impact of the impact of cooling methods to improve the study and ways to achieve the same flow of cooling gas to maintain the same conditions, to improve the cooling effect and reduce the performance requirements of the material. The calculation results show that the cooling requirement can be satisfied along the blade height direction when the jet hole number and pore diameter satisfy the relation of (4n-1) D = h within a certain aperture range. Column jet hole, can meet the cooling requirements of the chord region of the blade, the use of split-seam exhaust mode can eliminate the phenomenon of high temperature at the tail; deflector and blade spacing zn / D changes in 1.71 ~ 2.57, the inner and outer surface of the blade average temperature does not affect Large, and with the pitch becomes smaller, the maximum temperature on the inner and outer surfaces of the blade decreases, the minimum temperature will increase; the cooling effect will be better as the cooling gas temperature decreases or the flow rate increases.