推进技术 ›› 2010, Vol. 31 ›› Issue (6): 777-782.

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N2O/C3H8火炬式点火器试验研究

王栋,郭红杰,梁国柱,周海清,刘俊   

  1. 北京航空航天大学宇航学院;北京航空航天大学宇航学院;北京航空航天大学宇航学院;上海空间推进技术研究所;上海空间推进技术研究所
  • 发布日期:2021-08-15

Experimental investigation on nitrous oxide/propane ignition characteristics

  1. School of Astronautics,Beijing Univ.of Aeronautics and Astronautics,Beijing 100191,China;School of Astronautics,Beijing Univ.of Aeronautics and Astronautics,Beijing 100191,China;School of Astronautics,Beijing Univ.of Aeronautics and Astronautics,Beijing 100191,China;Shanghai Space Propulsion Research Inst.,Shanghai 200233,China;Shanghai Space Propulsion Research Inst.,Shanghai 200233,China
  • Published:2021-08-15

摘要: 为了研究氧化亚氮/丙烷的点火特性,在理论分析的基础上采用电激励火炬式点火方案并组建了实验系统,在不同的流量和余氧系数工况下进行了N2O(g)/C3H8(g),N2O(g)/C3H8(l)点火特性实验。结果表明:采用气液同轴离心式喷嘴的电激励火炬式点火方案可行,实现了低余氧系数下的点火。所设计的点火器在1J的点火能量下,N2O(g)/C3H8(g)在燃烧室压强为环境大气压条件下的成功点火余氧范围为0.222~0.321;N2O(g)/C3H8(l)在燃烧室平衡压强为0.50~0.65 MPa时成功点火余氧范围为0.299~0.407,并在平衡压强提高至1~1.3 MPa后成功地引燃主发动机。

关键词: 氧化亚氮;丙烷;离心喷嘴;点火特性+

Abstract: To investigate the ignition characteristics of nitrous oxide/propane,a current excitation torch igniter was designed based on theoretical analysis.Experiments were performed under different mass flow and excess-oxidizer coefficient for N2O(g)/C3H8(g) & N2O(g)/C3H8(l) ignition characteristics research.The results show that the igniter scheme with centrifugal injector is feasible and the ignition under low excess-oxidizer coefficient is achieved.With excitation energy 1J,N2O(g)/C3H8(g) igniter successful excess-oxidizer coefficient ranges from 0.222 to 0.321 under environmental pressure.N2O(g)/C3H8(l) igniter successful excess-oxidizer coefficient ranges from 0.299 to 0.407 under chamber equilibrium pressure between 0.50 and 0.65 MPa,and the main engine is ignited successfully while increasing the equilibrium pressure be from 1.0 to 1.3 MPa.

Key words: Nitr ous oxide;Propane;Centrifugal injector;Ignition characteristics+