进气畸变对冲压燃烧室性能影响实验研究  

Experimental investigation on performance of ramjet combustor with effects of inlet flow distortion

作　　者：何陈 邓远灏 康松 姜军 翟云超 王健 HE Chen;DENG Yuanhao;KANG Song;JIANG Jun;ZHAI Yunchao;WANG Jian(AECC Sichuan Gas Turbine Research Establishment,Chengdu 610500,China)

机构地区：[1]中国航发四川燃气涡轮研究院,四川成都610500

出　　处：《推进技术》2024年第6期147-153,共7页Journal of Propulsion Technology

摘　　要：为研究进口气流畸变对冲压燃烧室总压恢复系数、点火边界及燃烧效率等工作性能的影响,对冲压燃烧室模型实验件在均匀进口气流及3种不同的畸变进口气流条件下进行了冷态流阻实验、点火实验及燃烧性能实验。结果表明:进口流场畸变程度对冲压燃烧室的总压恢复系数影响较小;将点火电嘴设置在流场低压区,可以明显提高点火性能,在设计冲压燃烧室时,设置2支点火器并成两侧对称分布,可以保证始终有1支点火器位于流场低压区中,进而扩大点火边界;气流畸变对燃烧效率有明显影响,当进口马赫数大于0.15时,均匀来流燃烧效率略高于畸变来流;当进口马赫数小于0.15时,畸变来流燃烧效率高于均匀来流,其中畸变程度最大的畸变模拟孔板1可以使燃烧效率提高10%以上。In order to figure out the effects of the inlet flow distortion on the performance of ramjet combustor such as total pressure recovery coefficients,ignition boundary and combustion efficiency,cold flow experiments,ignition experiments and combustion experiments of ramjet combustor were carried out under the conditions of uniform inlet flow and 3 different distorted inlet flows.Results show that distortion degree of inlet flow has little influence on total pressure recovery coefficients of ramjet combustor.If the ignition nozzle is set in the low total pressure area,the ignition performance can be improved significantly.When designing the ramjet combustion chamber,it is better to arrange two igniters in a symmetrically position,which can ensure that there is always one igniter in the low total pressure area,thus expanding the ignition boundary.Inlet flow distortion has obvious influence on combustion efficiency.When the inlet Mach number is greater than 0.15,the combustion efficiency of uniform incoming flow is slightly higher than that of distorted incoming flow.When the inlet Mach number is less than 0.15,the combustion efficiency of distorted inflow is higher than that of uniform inflow,and the distorted simulated orifice plate 1 with the largest distortion can improve the combustion efficiency by more than 10%.

关 键 词：冲压燃烧室 进气畸变 总压恢复系数 点火性能 燃烧效率 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]