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| Modeling study to compare the flow and heat transfer characteristics of low-power hydrogen, nitrogen and argon arc-heated thrusters | |
Wang HX ; Chen X; Pan WX(潘文霞); Murphy AB; Geng JY; Jia SX
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| 发表期刊 | Plasma Science and Technology
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| 2010 | |
| 卷号 | 12期号:6页码:692-701 |
| ISSN | 1009-0630 |
| 摘要 | A modelling study is performed to compare the plasma °ow and heat transfer char- acteristics of low-power arc-heated thrusters (arcjets) for three di®erent propellants: hydrogen, nitrogen and argon. The all-speed SIMPLE algorithm is employed to solve the governing equa- tions, which take into account the e®ects of compressibility, Lorentz force and Joule heating, as well as the temperature- and pressure-dependence of the gas properties. The temperature, veloc- ity and Mach number distributions calculated within the thruster nozzle obtained with di®erent propellant gases are compared for the same thruster structure, dimensions, inlet-gas stagnant pressure and arc currents. The temperature distributions in the solid region of the anode-nozzle wall are also given. It is found that the °ow and energy conversion processes in the thruster nozzle show many similar features for all three propellants. For example, the propellant is heated mainly in the near-cathode and constrictor region, with the highest plasma temperature appear- ing near the cathode tip; the °ow transition from the subsonic to supersonic regime occurs within the constrictor region; the highest axial velocity appears inside the nozzle; and most of the input propellant °ows towards the thruster exit through the cooler gas region near the anode-nozzle wall. However, since the properties of hydrogen, nitrogen and argon, especially their molecular weights, speci¯c enthalpies and thermal conductivities, are di®erent, there are appreciable di®er- ences in arcjet performance. For example, compared to the other two propellants, the hydrogen arcjet thruster shows a higher plasma temperature in the arc region, and higher axial velocity but lower temperature at the thruster exit. Correspondingly, the hydrogen arcjet thruster has the highest speci¯c impulse and arc voltage for the same inlet stagnant pressure and arc current. The predictions of the modelling are compared favourably with available experimental results. |
| 学科领域 | 电磁流体力学和等离子体动力学 |
| DOI | 10.1088/1009-0630/12/6/11 |
| URL | 查看原文 |
| 收录类别 | SCI |
| 语种 | 英语 |
| WOS记录号 | WOS:000286172000011 |
| 引用统计 | |
| 文献类型 | 期刊论文 |
| 条目标识符 | http://dspace.imech.ac.cn/handle/311007/43284 |
| 专题 | 等离子体与燃烧中心(2009-2011) |
| 通讯作者 | Wang HX |
| 推荐引用方式 GB/T 7714 | Wang HX,Chen X,Pan WX,et al. Modeling study to compare the flow and heat transfer characteristics of low-power hydrogen, nitrogen and argon arc-heated thrusters[J]. Plasma Science and Technology,2010,12,6,:692-701. |
| APA | Wang HX,Chen X,潘文霞,Murphy AB,Geng JY,&Jia SX.(2010).Modeling study to compare the flow and heat transfer characteristics of low-power hydrogen, nitrogen and argon arc-heated thrusters.Plasma Science and Technology,12(6),692-701. |
| MLA | Wang HX,et al."Modeling study to compare the flow and heat transfer characteristics of low-power hydrogen, nitrogen and argon arc-heated thrusters".Plasma Science and Technology 12.6(2010):692-701. |
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