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基于PRO/Ⅱ的液态甲烷精馏设计与模拟

Design and simulation of distillation by PRO/Ⅱ for liquid methane purification
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摘要 为连续制取摩尔分数不低于99.999%、硫摩尔分数低于0.00001%的液态甲烷推进剂,提出了一种利用LNG连续式低温精馏提纯液态甲烷的设想,对该方案进行理论基础研究和计算,对流程中重要操作点进行了讨论。除采用简捷设计方法对精馏过程的主要参数进行计算外,还采用流程模拟软件PRO/Ⅱ对设计结果进行优化模拟。经简化和计算,脱氮塔需要10个理论分离级,而脱乙烷塔需要16个理论分离级。此外提出在精馏系统中引入制冷循环系统来利用相应低温流体介质的冷量,可作为相关工程方案的参考。 In order to obtain product with gross impurity less than 0. 001% and contains sulfur less than 0. 000 01% ,a method to continuously purify liquid methane from LNG was introduced,which based on cryogenic rectification technique. The theory of this precept was studied and some calculation work was done for it. Some important operation parameters of the flow were discussed in detail. Besides the calculation of main parameters,some simulation and optimization work was accomplished based on flow simulation software PRO/Ⅱ. It indicates that 10 theory trays are needed to move light element and 16 for the heavy components. Additionally,a cryogenic cycle was considered to utilize the cold in this system,and it can be a reference for some projects.
出处 《低温工程》 CAS CSCD 北大核心 2010年第4期53-57,共5页 Cryogenics
关键词 液态甲烷 LNG 低温精馏 PRO/Ⅱ软件 制冷循环 liquid methane LNG cryogenic rectification PRO/Ⅱ cryogenic cycle
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  • 1王鹏武.全流量补燃循环液氧/甲烷发动机系统分析[J].火箭推进,2004,30(6):15-18. 被引量:7
  • 2孙宏明.液氧/甲烷发动机评述[J].火箭推进,2006,32(2):23-31. 被引量:37
  • 3Philippart K D, Moser M D. Stability Analyses of Liquid Oxygen/Methane Injectors Using Currently Available Analytical Tools[R]. AIAA88-2851.
  • 4Judd D, Buccella S, Alkema M, et al. Development Testing of a LO2/Methane Engine for in-Space Propulsion [R]. AIAA 2006-5079.
  • 5Klepikov I A, Katorgin B L. The New Generation of Rocket Engines, Operating by Ecologically Safe Propellant Liquid Oxygen and Liquefied Natural Gas [R]. IAF-97-S.1.03.
  • 6Leudiere V, Supie P, Beaurain A, et al. KVD-1 Engine in LOX/CH4[R]. AIAA 2007-5446.
  • 7Zurbach S, Thomas J L. Recent Advances on LOX/ Methane Combustion for Liquid Roket Engine RejectorR]. AIAA 2002-4321.
  • 8Torano Y, Arita M, Takahashi H, et al. Current Study Status of the Advanced Technologies for the J-I Upgrade Launch Vehicle - LO2/LNG Engine [R]. AIAA 2001- 1783.
  • 9Kim K, Ju D. Development of Chase-10 Liquid Rocket Engine Having 10ft Thrust Using LO2 & LNG (Methane) [R]. AIAA 2006-4907.
  • 10[1]Rosenberg,S D Gage,M L.Compatibility of hydrocarbon fuels with booster engine combustion chamber liners[R].AIAA88-3215.

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