排序方式: 共有67条查询结果,搜索用时 0 毫秒
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燃料供给的实时、精确调节是冲压发动机技术研究的重点,对提高发动机的效率、改善发动机的工作性能具有重要的意义。为实现冲压发动机气态燃料在高温下流量的精确调节,提出了一种新型的拉瓦尔式燃料流量调节阀,以对流入发动机燃烧室的高温气态燃料进行流量调节。首先,开发了一种用于燃料供应的高温流量调节阀,然后通过采用有限元分析方法,分析了流经主阀阀口的气态燃料速度及压力的分布,从而找出了流量变化规律。研究结果表明,采用拉瓦尔管状阀口的流量调节阀,在不改变阀芯位移量以及一定入口压力条件下,流经阀口的燃料流量保持不变,且与出口压力无关。 相似文献
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Toru Takahashi Takayasu Fujino Motoo Ishikawa 《IEEJ Transactions on Electrical and Electronic Engineering》2013,8(5):440-445
Numerical analyses of the experimental‐scale scramjet engine driven magnetohydrodynamics generator implemented in the Hypersonic Vehicle Electric Power System project have been carried out to clarify plasma behaviors and power generation characteristics. Three‐dimensional numerical analyses have been performed under the two inlet conditions: one is the uniform inlet temperature condition, and the other is the nonuniform inlet temperature condition. Under the nonuniform inlet temperature condition, the generator performance approximately agrees with the experimental result. The tendency of the voltage loss is also reconstructed near the power takeoff electrodes though the voltage loss is smaller than that observed in the experimental result. The electric power output under the nonuniform inlet temperature condition is 40% smaller than that under the uniform inlet temperature condition. This is because the ratio of the Joule dissipation to the work by the Lorentz force increases owing to the decrease of active generator region as the current concentrates in the high‐temperature region when the inlet temperature nonuniformity is considered. © 2013 Institute of Electrical Engineers of Japan. Published by John Wiley & Sons, Inc. 相似文献
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采用RNGκ-ε湍流模型以及有限速率化学动力学模型,求解了二维Navier-Stokes方程,分别以氢气和乙烯为燃料数值模拟了具有双台阶单凹槽的超燃冲压发动机燃烧室的流场,并与试验数据进行了对比。计算结果表明:双台阶下游和凹槽处出现了有利于燃烧和火焰稳定的回流区;在隔离段入口马赫数2.0左右时,该燃烧室可以实现在亚燃和超燃两种模态下工作,燃烧效率在0.7以上;数值模拟壁面压力分布的结果与相应的试验结果吻合良好。 相似文献
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