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以高温气冷堆氦气轴流压气机叶型气动特性为研究对象,结合优化算法与现代流场模拟技术研究了氦气压气机叶型的设计特点和损失特性。数值模拟采用SST湍流模型和γ-Reθ转捩模型,考虑了氦气附面层转捩对叶型损失的影响。对比低速空气压气机叶型和CDA叶型,研究了具有低损失和宽广工作范围的氦气压气机叶片表面压力分布特点及其附面层发展特点。研究结果表明,优化叶型在保持设计工况下损失基本不变的情况,大幅度地增加了氦气叶型的低损失攻角范围,并减小了不同攻角时叶型的落后角。优化叶型在正攻角情况下,附面层转捩显著推迟,氦气压气机叶型损失得到有效控制。
The aerodynamic characteristics of helium axial compressor blades in high temperature gas cooled reactors were studied. The design characteristics and loss characteristics of helium compressor blades were studied by combining the optimization algorithm and modern flow field simulation. The SST turbulence model and the γ-Reθ transition model are used in the numerical simulation, and the influence of the rotation of helium on the leaf loss is considered. Contrasting the low-speed air compressor blades and the CDA airfoils, the surface pressure distribution characteristics of the helium compressor blades with low loss and wide working range and the development characteristics of their surface coatings were studied. The results show that the loss of the optimized blade shape under the condition of maintaining the design condition is substantially unchanged, the range of low loss angle of attack of the helium blade type is greatly increased, and the falling angle of the blade pattern at different angles of attack is reduced. Optimized leaf type in the case of positive angle of attack, stratum transfer is significantly delayed, helium compressor blade loss is effectively controlled.