Investigation on turbine inter-vane combustion performance based on fuel cooled vane
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摘要:
为进一步提升航空燃气涡轮发动机性能，提出一种高压涡轮叶间燃烧的结构，采用叶片油冷后的高温燃油喷入叶间通道燃烧，利用径向槽（radial vane cavity，RVC）稳定火焰，以涡轮导向叶片C3X为叶间燃烧叶片模型，数值研究了径向槽尺寸（深长比为0.4～0.6）、油气比（0.007～0.0105）和燃油温度（300～500 K）对叶间燃烧性能的影响。结果表明：径向槽深长比为0.5时获得最佳燃烧效果，由燃烧引起的热阻损失在7%左右，可实现在叶间的近似等温燃烧；叶间燃烧性能随油气比增大而降低，油气比为0.007时距叶片出口 20 mm处燃烧效率达到98.86%；高温燃油在叶间通道内燃烧性能要明显优于低温燃油的燃烧性能，在叶片出口处燃烧效率提升约13%。相关结论可为叶间燃烧技术的发展提供参考。
Abstract:To expand the performance of aero-gas turbine engine, a structure of high-pressure turbine inter-vane combustion was proposed. The high-temperature fuel was injected into the inter-vane channel after cooling the vane. And the flame was stabilized by radial vane cavity (RVC). The C3X turbine guide vane was used as the inter-vane combustion model and the effects of radial vane cavity (depth length ratio 0.4−0.6), fuel-air ratio (0.007−0.0105) and fuel temperature (300−500 K) on inter-vane combustion performance were numerically studied. It was observed that the optimization combustion effect was obtained with depth length ratio 0.5. The thermal resistance loss caused by combustion was about 7%, which can realize the approximately isothermal combustion between the vanes. The inter-vane combustion performance decreased with the increase of fuel-air ratio, and the combustion efficiency reached 98.86% at 20 mm away from the blade outlet when the fuel-air ratio was 0.007. The combustion performance of high-temperature fuel in the inter-vane channel was better than that of low-temperature fuel, and the combustion efficiency at the outlet of the blade increased about 13%. The conclusions can provide a reference for the development of inter-vane burner technology.
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图 8 不同径向槽尺寸冷态流场沿程流动特性
Figure 8. Flow characteristics of cold flow field with different radial vane cavity sizes
图 9 不同径向槽尺寸燃烧流场沿程流动与燃烧特性
Figure 9. Flow and combustion characteristics of combustion flow field with different radial vane cavity sizes
图 10 不同径向槽尺寸沿程燃烧效率
Figure 10. Combustion efficiency along the way with different radial vane cavity sizes
图 11 不同径向槽尺寸出口径向总温分布
Figure 11. Radial total temperature distribution at the outlet with different radial vane cavity sizes
图 12 不同径向槽尺寸中截面流场结构
Figure 12. Medium section flow field structure with different radial vane cavity sizes
图 13 不同径向槽尺寸上端壁温度场
Figure 13. Temperature field of upper face with different radial vane cavity sizes
图 14 D/L=0.5时冷态流场与燃烧流场沿程平均静温
Figure 14. Average static temperature of cold and combustion flow field with D/L =0.5
图 15 不同油气比燃烧流场流动特性
Figure 15. Flow characteristics of combustion flow field with different fuel-air ratios
图 16 不同油气比燃烧流场燃烧特性
Figure 16. Combustion characteristics of combustion flow field with different fuel-air ratios
图 17 不同油气比出口径向总温分布
Figure 17. Radial total temperature distribution at the outlet with different fuel-air ratios
图 18 不同燃油温度沿程总压恢复系数
Figure 18. Total pressure recovery coefficient along the way with different fuel temperatures
图 19 不同燃油温度燃烧流场燃烧特性
Figure 19. Combustion characteristics of combustion flow field with different fuel temperatures
图 20 不同燃油温度沿程CO与CO2体积分数
Figure 20. Volume fraction of CO and CO2 along the way with different fuel temperatures
表 2 边界参数
Table 2. Boundary parameters
边界条件参数 数值 主流进口总压/Pa 413286 主流进口总温/K 818 主流出口静压/Pa 254172 主流进口湍流强度 8.3 主流进口湍流黏性比 30 前后壁冷气流量/（kg/s） 0.0068 尾缘劈缝流量/（kg/s） 0.020 
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