期刊文献+

碳氢燃料超燃冲压发动机油气涡轮做功能力评估 被引量:4

Evaluation of Fuel Vapor Turbine Capacity for Doing Work Onboard for a Hydrocarbon Fueled Scramjet
在线阅读 下载PDF
导出
摘要 为了研究油气涡轮泵燃油供给系统中,碳氢燃料裂解油气的做功能力,以正癸烷为替代燃料,基于其裂解后的实验组分分析,发展了基于Soave-Redlich-Kwong(SRK)状态方程的真实气体裂解混合物的等熵焓降计算方法,并对油气涡轮的做功能力进行了分析和评估。研究表明,当膨胀起始温度为950K,膨胀起始压力超过3MPa,膨胀比为2时,裂解混合物的等熵焓降可达110kJ/kg,具备较强的做功能力。 To evaluate the fuel vapor capacity for doing work in fuel vapor turbopumpfeeding system, ndeeane was selected as surrogate fuel and experimental tests were firstly carried out to discover the components information of cracked fuel vapor at various thermophysical conditions. The thermophysical properties of real fuel vapor were then calculated by Soave-Redlich-Kwong (SRK) equation of state. At last, the isen- tropic enthalpy drop of real fuel vapor was calculated. With an initial temperature of 950K and an initial pressure over 3MPa, an isentropic enthalpy drop of 110kJ/kg is available when the expansion ratio is 2, which indicates that strong capacity for doing work can be achieved.
出处 《推进技术》 EI CAS CSCD 北大核心 2013年第12期1708-1712,共5页 Journal of Propulsion Technology
关键词 超燃冲压发动机 碳氢燃料 油气涡轮 等熵焓降 Scramjet Hydrocarbon fuels Fuel vapor turbine Isentropic enthalpy drop
  • 相关文献

参考文献15

  • 1闫国军,杨朗,董泳,鲍文.冲压发动机涡轮泵建模及能耗分析[J].节能技术,2006,24(3):257-260. 被引量:4
  • 2安庆芳.冲压空气涡轮泵供油系统的自然配合供油规律[J].推进技术,1986,7(5):42-48.
  • 3安庆芳.空气涡轮在弹上的取气问题[J].推进技术,1985.6(4):74-79.
  • 4David P, Thomas F, Dan G, et al. Design, Fabrication and Testing of an Actively Cooled Scramjet Propulsion System [R]. AIAA 2003-0015.
  • 5Powell O A, Edwards J T,Norris R B, et al. Develop-ment of Hydrocarbon-Fueled Scramjet Engines: The Hy- personic Technology (nyTech) Program [ J]. Journal of Propulsion and Power, 2001, 17 (6) :1170-1176.
  • 6牛文,李文杰.美国空军圆满完成X-51A第四次试飞[J].飞航导弹,2013(5):3-4. 被引量:11
  • 7Daniau E, Bouchez M,Bounaceur R, et al. Contribution to Scramjet Active Cooling Analysis Using n-Dodecane Decomposition Model as a Generic Endothermic Fuel [ R]. AIAA 2003-6920.
  • 8Castaldi M J, Leylegian J C,Chinitz W, et al. Develop- ment of an Effective Endothermic Fuel Platform for Regen- eratively-Cooled Hypersonic Vehicles [ R ]. AIAA 2006- 4403.
  • 9T Kanda, G Masuya, Y Wakamatsu, et ah A Comparison of Scramjet Engine Performances Among Various Cycles [ R]. AIAA 89-2676.
  • 10T Kanda, G Masuya,Y Wakamatsu. Propellant Feed Sys- tem of a Regeneratively Cooled Seramjet [ J]. Journal of Propulsion and Power, 1991 , 7(2) : 299-301.

二级参考文献7

  • 1祁彦伟.浅谈离心泵变频调速节能[J].节能技术,2005,23(5):477-479. 被引量:13
  • 2刘兴洲.飞航导弹动力装置[M].北京:宇航出版社,1992..
  • 3张远君.液体火箭发动机涡轮泵设计[M].北京:北京航空航天大学出版社,1995..
  • 4王仲奇,秦仁.透平机械原理[M].哈尔滨:哈尔滨工业大学出版社,1979.
  • 5Daryl Mayer. X-51 A Waverider achieves breakthrough in final flight[OL].http://www.af.mil/news/story.asp? id =123346970,2013.
  • 6Guy Norris. X-51A Waverider Achieves Hypersonic Goal On Final Flight[OL].http://www.aviationweek.com/Article.aspx? id =/article-xml/awx 05 02 2013_p0-575769.xml,2013.
  • 7严飞,牛文,叶蕾.美空军积极推进高速打击武器(HSSW)项目[J].战术导弹技术,2013(3):9-12. 被引量:4

共引文献13

同被引文献40

引证文献4

二级引证文献39

相关作者

内容加载中请稍等...

相关机构

内容加载中请稍等...

相关主题

内容加载中请稍等...

浏览历史

内容加载中请稍等...
;
使用帮助 返回顶部