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首页> 外文会议>AIAA/SAE/ASEE joint propulsion conference >Applicability of a LOx Vaporization Preburner for Swirling-Flow Hybrid Rocket Engines
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Applicability of a LOx Vaporization Preburner for Swirling-Flow Hybrid Rocket Engines

机译：LOX汽化预燃烧器适用于旋流式混合火箭筒发动机的应用

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One of the key technologies to actualize our proposing swirling-flow hybrid rocket engine is to develop a GOx feed system using the LOx vaporizer. The burning experiment of the LOx vaporization preburner has been conducted to obtain the fundamental characteristics for the feed system. The LOx vaporization preburner uses a multi-port PMMA fuel grain. The results showed two types of combustion behavior of the preburner. One was combustion at the lower surface of the PMMA grain. Since the LOx flow velocity was too high, the flame could not travel toward the upstream of the grain port. The other was combustion at the upper surface of the grain. The flame formed in the grain port and the regression rates of each port were ranged from 0.31 to 0.36 mm/s. The burning at the grain lower surface was considered to be preferable for the long duration vaporization under a constant O/F and the continuous burning was attained at extensively low O/F value of 286. The regression rate of the lower surface was 0.14 mm/s at the LOx flow rate of 85.8 g/s.
机译：实现我们提出的旋流混合火箭发动机的关键技术之一是使用LOX蒸发器开发GOX馈送系统。已经进行了LOX汽化预燃烧剂的燃烧实验，以获得饲料系统的基本特征。 LOX汽化预燃烧剂使用多端口PMMA燃料颗粒。结果表明了预燃烧剂的两种燃烧行为。一个是PMMA晶粒的下表面处的燃烧。由于LOX流速太高，因此火焰无法朝向纹理的上游行进。另一个是谷物上表面的燃烧。形成在纹理端口中的火焰和每个端口的回归速率范围为0.31至0.36mm / s。认为谷粒下表面的燃烧是优选的，对于恒定的O / F下的长持续时间蒸发，并且连续燃烧以广泛的低O / F值达到286.下表面的回归速率为0.14mm / S以85.8 g / s的LOX流速。

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