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Modeling study on the flow, heat transfer and energy conversion characteristics of low-power arc-heated hydrogen/nitrogen thrusters
Wang HX; Geng JY; Chen Xi; Pan WX(潘文霞)
Source PublicationPlasma Chemistry and Plasma Processing
2010
Volume30Issue:6Pages:707-731
ISSN0272-4324
AbstractA modeling study is conducted to investigate the effect of hydrogen content in propellants on the plasma flow, heat transfer and energy conversion characteristics of low-power (kW class) arc-heated hydrogen/nitrogen thrusters (arcjets). 1:0 (pure hydrogen), 3:1 (to simulate decomposed ammonia), 2:1 (to simulate decomposed hydrazine) and 0:1 (pure nitrogen) hydrogen/nitrogen mixtures are chosen as the propellants. Both the gas flow region inside the thruster nozzle and the anode-nozzle wall are included in the computational domain in order to better treat the conjugate heat transfer between the gas flow region and the solid wall region. The axial variations of the enthalpy flux, kinetic energy flux, directed kinetic-energy flux, and momentum flux, all normalized to the mass flow rate of the propellant, are used to investigate the energy conversion process inside the thruster nozzle. The modeling results show that the values of the arc voltage, the gas axial-velocity at the thruster exit, and the specific impulse of the arcjet thruster all increase with increasing hydrogen content in the propellant, but the gas temperature at the nitrogen thruster exit is significantly higher than that for other three propellants. The flow, heat transfer, and energy conversion processes taking place in the thruster nozzle have some common features for all the four propellants. The propellant is heated mainly in the near-cathode and constrictor region, accompanied with a rapid increase of the enthalpy flux, and after achieving its maximum value, the enthalpy flux decreases appreciably due to the conversion of gas internal energy into its kinetic energy in the divergent segment of the thruster nozzle. The kinetic energy flux, directed kinetic energy flux and momentum flux also increase at first due to the arc heating and the thermodynamic expansion, assume their maximum inside the nozzle and then decrease gradually as the propellant flows toward the thruster exit. It is found that a large energy loss (31-52%) occurs in the thruster nozzle due to the heat transfer to the nozzle wall and too long nozzle is not necessary. Modeling results for the NASA 1-kW class arcjet thruster with hydrogen or decomposed hydrazine as the propellant are found to compare favorably with available experimental data.
Subject Area电磁流体力学和等离子体动力学
DOI10.1007/s11090-010-9257-0
URL查看原文
Indexed BySCI
Language英语
WOS IDWOS:000284122900001
WOS KeywordLASER-INDUCED FLUORESCENCE ; TRANSPORT-COEFFICIENTS ; NONEQUILIBRIUM ; HYDROGEN ; PERFORMANCE ; TECHNOLOGY ; PLASMAS ; NOZZLE ; ARGON
WOS Research AreaEngineering ; Physics
WOS SubjectEngineering, Chemical ; Physics, Applied ; Physics, Fluids & Plasmas
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Document Type期刊论文
Identifierhttp://dspace.imech.ac.cn/handle/311007/43283
Collection等离子体与燃烧中心(2009-2011)
Corresponding AuthorWang HX
Recommended Citation
GB/T 7714
Wang HX,Geng JY,Chen Xi,et al. Modeling study on the flow, heat transfer and energy conversion characteristics of low-power arc-heated hydrogen/nitrogen thrusters[J]. Plasma Chemistry and Plasma Processing,2010,30(6):707-731
APA Wang HX,Geng JY,Chen Xi,&潘文霞.(2010).Modeling study on the flow, heat transfer and energy conversion characteristics of low-power arc-heated hydrogen/nitrogen thrusters.Plasma Chemistry and Plasma Processing,30(6),707-731.
MLA Wang HX,et al."Modeling study on the flow, heat transfer and energy conversion characteristics of low-power arc-heated hydrogen/nitrogen thrusters".Plasma Chemistry and Plasma Processing 30.6(2010):707-731.
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