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首页> 外文会议>AIAA/ASME/SAE/ASEE joint propulsion conference exhibit >Fuel Regression Rate Behavior for Various Fuels in Swirling-Oxidizer-Flow-Type Hybrid Rocket Engines
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Fuel Regression Rate Behavior for Various Fuels in Swirling-Oxidizer-Flow-Type Hybrid Rocket Engines

机译：旋流氧化流式混合火箭发动机中各种燃料的燃料回归率行为

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In order to clarify the overall and local fuel regression rate behavior of hybrid combustion in swirling oxidizer flow, burning tests of the swirling-oxidizer-flow-type hybrid rocket engine were conducted using PP , PMMA and WAX fuel grains. The experiments showed that for all fuels, the relation between the time-averaged overall fuel regression rate, r_(over), and the intermediate oxygen mass flux, G_(oltm), was expressed by a conventional hybrid regression rate formula such as r_(ovet) = aG_(oltm)~n. The values of a and n differed according to the fuel type. The n values implied that the combustion in the PMMA grains occurred by the diffusion-limited combustion mechanism, and that the gas-phase reaction rate of PP was slower than that of PMMA. For PP grains, the n values at the grain leading edge were smaller than those at the rear grain region. While the local fuel regression rate, r_(loc), at the rear region decreased slightly with increasing the burning time t_b, r_(loc) at the leading edge was independent of t_b. These results suggested that the combustion mechanisms at the leading edge and the rear region differed.
机译：为了弄清混合燃烧在涡流氧化剂流中的整体和局部燃料回归速率特性，使用PP，PMMA和WAX燃料颗粒进行了涡流氧化剂流式混合火箭发动机的燃烧试验。实验表明，对于所有燃料，时间平均总体燃料回归率r_（over）和中间氧气质量通量G_（oltm）之间的关系由常规混合回归率公式表示，例如r_（ ovet）= aG_（oltm）〜n。 a和n的值根据燃料类型而有所不同。 n值表示PMMA晶粒中的燃烧是通过扩散限制燃烧机理发生的，并且PP的气相反应速率比PMMA的气相反应速率慢。对于PP晶粒，晶粒前缘的n值小于后晶粒区的n值。随着燃烧时间t_b的增加，后部区域的局部燃料回归率r_（loc）略有下降，而前沿的r_（loc）与t_b无关。这些结果表明在前缘和后部区域的燃烧机理是不同的。

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