首页|针栓结构参数对液氧/甲烷发动机跨临界燃烧效率的影响

针栓结构参数对液氧/甲烷发动机跨临界燃烧效率的影响

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为了研究跨临界燃烧下针栓结构参数对燃烧效率的影响,采用标准k-ε湍流模型、非绝热稳态扩散火焰面模型,同时考虑流体真实物性,对液氧/甲烷针栓式发动机跨临界燃烧进行数值研究.分析不同物性计算方法对推力室内流场影响,并分析针栓喷注器径向环缝宽度、轴向环缝宽度对发动机燃烧效率的影响.结果表明:考虑跨临界效应时,形成的中心回流区和高温区域均较小.在一定范围内,径向环缝增大,燃烧效率先减小后增大,轴向环缝宽度增大,燃烧效率降低,轴向环缝宽度取较小值而径向环缝宽度取较大值时,可获得较高的燃烧效率.动量比小于1时,增大轴向动量可有效改善混合;动量比大于1时,增大轴向动量对改善混合的作用减弱.燃烧效率随动量比增大而降低,当不同工况的动量比值接近时,总动量较大工况的燃烧效率更高.
Structural parameters of pintle on transcritical combustion efficiency of liquid oxygen/methane engine
To study the effects of pintle structural parameters on the combustion efficiency in transcritical combustion,a standard k-ε turbulence model and a non-adiabatic stable diffusion flamelet model were utilized to numerically study the transcritical combustion of an LOX/CH4 pintle engine considering the real gas properties of fluid.The study analyzed the impact of various methods for calculating physical properties on the flow field within the thrust chamber,and the effects of radial and axial annular seam width of pintle injector on engine combustion efficiency were analyzed.The results showed that the size of both the central recirculation zone and the high temperature zone was reduced when considering the transcritical effect.Within a certain range,as the radial annular seam width increased,the combustion efficiency initially decreased and then increased,as the axial annular seam width increased,the combustion efficiency decreased.A greater combustion efficiency can be achieved by reducing the axial annular seam width and increasing the radial annular seam width.When the total momentum ratio was less than 1,increasing axial momentum can effectively improve mixing.However,if the total momentum ratio was greater than 1,increasing axial momentum can hinder the improvement of mixing.The combustion efficiency decreased with the increase of the total momentum ratio.When the total momentum ratio for different operating conditions was similar,the operating condition with a higher momentum ratio exhibited a higher combustion efficiency.

LOX/CH4 rocket enginepintle injectorstranscritical combustionstructural parameterscombustion efficiency

谭天军、张斌、李志强、向纪鑫、徐吉峰、任和、郑晓霞

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太原理工大学机械与运载工程学院,太原 030024

中国人民解放军空军装备部太原军事代表处,太原 030000

太原理工大学航空航天学院,太原 030600

中国商用飞机有限责任公司北京民用飞机技术研究中心,北京 102211

中国商用飞机有限责任公司营销中心,上海 200126

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液氧/甲烷火箭发动机 针栓式喷注器 跨临界燃烧 结构参数 燃烧效率

山西省应用基础研究计划面上青年项目山西省应用基础研究计划面上青年项目山西省高等学校科技创新项目山西省关键核心技术和共性技术研发攻关专项山西省科技重大专项

20210302124681202103021243852021L0692020XXX017202101120401007

2024

10.13224/j.cnki.jasp.20220825

航空动力学报
中国航空学会

航空动力学报

CSTPCD北大核心
影响因子：0.59
ISSN：1000-8055
年,卷(期)：2024.39(9)
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