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摘要:
针对气冷涡轮叶片的多场耦合特性，利用流热耦合（CHT）方法，对采用不同气冷结构的高压涡轮导叶进行数值模拟。在内冷涡轮导叶算例中，对比实验数据选取精度较高的流热耦合计算方案，分析该内冷涡轮导叶的多场特性及耦合机理。在此基础上，以带有气膜冷却孔及内冷通道的气冷涡轮导叶为研究对象，重点围绕冷却射流与主流的相互作用，讨论近壁边界层中流热耦合关系及气冷效率影响因素等相关问题。结果表明：采用流热耦合计算方法及合适的湍流转捩模型有利于提高数值精度；气冷涡轮导叶的流场温度场密切耦合，流动换热特性互相影响；冷气射速低时，增加冷气流量可提高气膜冷却效率，冷气量达到一定值时，冷气流量增加将导致气膜冷却孔后上游冷却效果变差，下游冷却效果变好；冷气射速较高时，将与主流相互作用产生复杂流动结构（如肾形涡、马蹄涡等），对温度分布存在一定影响。
Abstract:According to the multi-field coupling characteristics of air-cooled turbine blades, numerical simulation of high-pressure turbine guide vanes with different air-cooling structures is carried out by the flow-heat coupling method. In internal cooling turbine blade example, by comparing the experimental data to select a higher-accuracy Conjugate Heat Transfer (CHT) calculation scheme, the multi-field characteristics and coupling mechanism of the internal cooling guide vane are analyzed. On this basis, the turbine guide vanes with film cooling holes and internal cooling channels are the research object, the interaction between cooling jet and main stream are focused on, and the fluid thermal coupling relationship in near wall boundary layer and related questions such as the factors affecting the air cooling efficiency are discussed. The results show that the use of flow-heat coupling calculation method and a suitable turbulent transition model is conducive to improving the simulation accuracy. Flow field and temperature field of the air-cooled guide vane are closely coupled, and the flow heat-transfer characteristics affect each other. In case of low speed rate, increased cool air flow can improve the cooling efficiency of the film, and if the flow of cold air is increased to a certain value, the increase in the cold flow will cause a poor upstream cooling effect behind the air-cooled hole and a better downstream cooling effect. High-speed cooling interacts with main stream, which will produce complex flow structures such as kidney-shaped vortices and horseshoe vortices that have certain influences on temperature distribution.
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Key words:
- high-pressure turbine /
- Conjugate Heat Transfer (CHT) /
- film cooling /
- flow field structure /
- CFD
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图 1 MARK Ⅱ几何气动外形及内冷结构编号示意图
Figure 1. MARKⅡgeometry and schematic diagram of internal cooling structure numbering
图 3 不同壁温条件下叶表温度分布曲线
Figure 3. Surface temperature distribution curves of blade under different wall temperature conditions
图 4 不同计算模型求解的叶表温度分布曲线
Figure 4. Surface temperature distribution curves of blade solved by different calculation models
图 5 不同PrT条件求解的叶表温度分布曲线
Figure 5. Surface temperature distribution curves of blade solved under different PrT conditions
图 10 流体域及叶片内部温度分布云图
Figure 10. Temperature distribution contour in fluid domain and blade interior
图 17 改型MARKⅡ叶表马赫数云图
Figure 17. Contour of Mach number at surface of retrofittedMARKⅡblade
图 19 不同吹风比下压力面温度分布
Figure 19. Temperature distribution of pressure surface under different blowing ratios
图 20 不同冷气射速下气膜冷却孔下游流线放大图
Figure 20. Enlarged streamline distribution of downstream hole at different flow velocities of cold air
图 21 高速射流条件下不同位置横向流线发展过程
Figure 21. Development of transverse streamlines at different positions under high-speed jet conditions
图 22 高速射流条件下受剪切作用形成的二次涡对
Figure 22. Secondary vortex pair induced by shear under high-speed jet conditions
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