提出一种具有盘腔扰流柱群的双辐板涡轮盘，利用靠近盘腔出口处叉排扰流柱群的强化对流换热，进一步提高了双辐板涡轮盘的换热效果。对壁面层网格进行细化，采用SST-k-ω湍流模型，分别建立具有光滑盘腔、盘腔扰流柱群的双辐板涡轮盘对流换热模型，分析了扰流柱群对盘腔对流换热的影响。对比分析表明:扰流柱群明显增加了盘腔的局部对流换热，辐板上的低温区域明显增加，涡轮盘的最高温度相应降低，最高温度降低4 K；随着雷诺数的增加，扰流柱群局部对流换热系数相应增加，盘腔内壁的面积平均换热系数提高了20%，增强了双辐板涡轮盘的降温效果。

In order to improve the convective heat transfer effect of traditional twin web turbine disk,the twin web turbine disk with staggered pin fins in cavity is developed in this work.It takes the advantage of enhanced convective heat transfer of pin fins.The convective heat transfer analysis model for traditional twin web turbine disk and the new twin web turbine disk with staggered pin fins in cavity are created with refined boundary layer grids.The SST-k-ωmodel is used for turbulence model and the influence of pin fins on convective heat transfer at cavity is analyzed.The results show that the convective heat transfer analysis method proposed in this work is in good agreement with theoretical analysis of the rotating disc cavity.The convective heat transfer analysis results of twin web turbine disk with staggered pin fins in cavity show that the local convective heat transfer coefficient near pin fins increases,the area of low temperature region in the two webs also increases and the maximum temperature of turbine disk is decreased 4K.With the increase of the inlet Reynolds number,convective heat transfer coefficient near pin fins increases,enhancing the convective heat transfer effect of twin web turbine disk with staggered pin fins.The local area-averaged heat transfer coefficient of the inner cavity surface is increased by 20%,improving the cooling effect of twin-web turbine disk.

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国家自然科学基金(51575444)；航空动力基金(6141B090319)；航天科学技术基金(2017-HT-XGD)