基于油冷叶片的涡轮叶间燃烧性能研究
Investigation on turbine inter-vane combustion performance based on fuel cooled vane
卿黎明 1朱剑琴 1程泽源1
作者信息
- 1. 北京航空航天大学能源与动力工程学院,北京 100191;北京航空航天大学航空发动机气动热力国家级重点实验室,北京 100191
- 折叠
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 20mm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.
关键词
涡轮叶间燃烧/油冷叶片/高温燃油/径向槽/燃烧性能/超紧凑燃烧Key words
turbine inter-vane burner/fuel cooled vane/high-temperature fuel/radial vane cavity/combustion performance/ultra-compact combustion引用本文复制引用
基金项目
中央高校基本科研业务费专项(501LKQB2022104013)
出版年
2024
NETL
NSTL
万方数据