O_(2)/PE固液混合发动机燃烧效率数值计算  

Numerical Calculation of Combustion Efficiency of O_(2)/PE Hybrid Rocket Motors

作　　者：胡峰[1,2] 王印 王栋 刘雪莉 王新强[1] HU Feng;WANG Yin;WANG Dong;LIU Xue-li;WANG Xin-qiang(Xi′an Changfeng Electromechanical Institute,Xi′an 710065,China;National Key Laboratory of Solid Rocket Propulsion,Northwestern Polytechnical University,Xi′an 710072,China)

机构地区：[1]西安长峰机电研究所,陕西西安710065 [2]西北工业大学固体推进全国重点实验室,陕西西安710072

出　　处：《火炸药学报》2025年第3期279-286,I0006,共9页Chinese Journal of Explosives & Propellants

摘　　要：基于燃气与固体燃料的耦合传热,建立了固液混合发动机燃烧室内流场数值计算模型,以聚乙烯(PE)为燃料、氧气为氧化剂研究了氧气旋流强度、氧气流强和燃烧室压强对燃烧效率的影响。结果表明,氧气直流喷注时,火焰距离燃面较远且后燃烧室中气相反应集中在氧含量较高的轴线附近,使后燃烧室凹腔存在较多燃料残留,导致发动机燃烧效率较低;喷注器旋流数大于0.2后,旋流喷注可显著强化气相掺混,当旋流数由0.167增大到0.444时,燃烧效率可提高5.25%;氧气入口流强每增加25kg/(m^(2)·s),燃烧效率以约1.1%的幅度提升;燃烧室压强对发动机燃烧效率和燃面退移速率的影响均较小。A numerical computational model of the hybrid rocket motors was established based on the heat transfer between gas and solid fuel,the effects of oxygen swirl intensity,oxygen mass flux and combustion chamber pressure on the combustion efficiency were studied using polyethylene as fuel and oxygen as oxidant.The results show that the flame is far from the burning surface and the gas reaction mainly occurs near the axis of high oxygen content when oxidizer is injected in rectilinear form,causing a significant amount of fuel residue in the rear combustion chamber cavity,which leads to a low combustion efficiency.A significant advantage in enhancing the gas mixing is exhibited as S>0.2,and the combustion increases by 5.25%when S increases from 0.167 to 0.444.The combustion efficiency increases by 1.1%with the increase of 25kg/(m^(2)·s)in the mass flux of O_(2).Chamber pressure has little influence on the combustion efficiency and burning surface regression rate.

关 键 词：物理化学 固液混合发动机 燃烧效率 数值计算 旋流强度 氧气流强 对流传热 扩散燃烧 

分 类 号：TJ55[兵器科学与技术—军事化学与烟火技术] V435[航空宇航科学与技术—航空宇航推进理论与工程]