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文摘
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为了测量超燃冲压发动机燃烧室的热环境,从Gardon热流计原理出发,发展了一套水冷热流/壁温一体化测量技术。采用热阻分析方法,对传感器的热结构进行了分析与优化设计。测试了多种隔热与外壳材料对传感器响应特性的影响。通过辐射加热方式对传感器进行了标定,获得了热流/电压、壁温/热流的标定曲线。采用该传感器,在模拟马赫数6、总温1800K的来流条件下,对超声速燃烧室的热环境进行了初步测量,获得了与传热分析相一致的结果。 |
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其他语种文摘
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To study the thermal environment of a scramjet combustor,a water-cooled heat flux/wall temperature measurement technique has been developed based on the principle of Gardon heat-flux sensor.Method of heat resistance analysis has been used to design the thermal structure of the sensor.Effects of materials and structure on the sensor’s responses have been determined.Calibration processes using radiative heating sources were carried out and calibration curves of heat flux vs voltage and wall temperature vs heat flux were obtained.Preliminary measurements were carried out on a supersonic combustor at flow conditions of Mach 6 at total temperature 1800K.The experimental results showed a good agreement with that of a heat transfer analysis. |
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来源
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实验流体力学
,2012,26(1):93-99 【核心库】
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关键词
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热流
;
壁温
;
热阻
;
超声速燃烧
;
热环境
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地址
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中国科学院力学研究所, 中国科学院高温气体动力学重点实验室, 北京, 100190
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语种
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中文 |
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文献类型
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研究性论文 |
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ISSN
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1672-9897 |
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学科
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航空 |
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基金
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国家自然科学基金重点项目
;
国家自然科学基金创新研究群体项目
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文献收藏号
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CSCD:4465536
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