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边界层控制方法降低喷管喉衬烧蚀影响因素研究

Study on nozzle boundary-layer control system for mitigating influence factors of nozzle throat erosion

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【作者】 王立武陈林泉刘勇琼武渊

【Author】 WANG Li-wu;CHEN Lin-quan;LIU Yong-qiong;WU Yuan;The 41st Institute of the Fourth Institute of CASC;Xi’an Aerospace Composites Material Institute;

【机构】 中国航天科技集团公司四院四十一所西安航天复合材料研究所

【摘要】 引入一种边界层控制方法,通过在喷管内表面形成一层低温富燃边界层,降低喷管内表面的温度和近壁面处氧化组分的浓度。采用二维轴对称模型对边界层控制方法进行了参变量研究,模拟了低温富燃气体的喷射质量、喷射温度、喷射位置和喷射角度对该方法的影响规律,比较了不同参变量对降低喷管内表面温度和近壁面处氧化组分浓度的效果,证明了边界层控制方法降低喷管喉衬烧蚀影响因素的有效性。

【Abstract】 A nozzle boundary-layer control system was introduced. This design can reduce the temperature of nozzle throat surface and the mass fractions of the oxidizing species in the combustion products due to the formation of a low-temperature fuel-rich boundary-layer. A parametric study of the effect of injection angle,geometric orientation,temperature and mass on the nozzle boundary-layer system was carried out using an axisymmetric model. A comparison of the decrease of nozzle surface temperature and concentrations of oxidizing species near nozzle surface under different parametric conditions was conducted. The change regulation of nozzle surface temperature and concentrations of oxidizing species near nozzle surface under different parametric conditions was elaborated. Finally,the effectiveness of nozzle boundary-layer control system on mitigating the influence factors of throat erosion was demonstrated.

【基金】 国家自然科学基金(51376166)
  • 【文献出处】 固体火箭技术 ,Journal of Solid Rocket Technology , 编辑部邮箱 ,2015年01期
  • 【分类号】V435
  • 【下载频次】114
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