空间发动机MMH/N_(2)O_(4)喷雾-燃烧-耦合传热过程模拟研究  

Numerical Investigation on Spray Combustion and Conjugate Heat Transfer of MMH/N_(2)O_(4)in Space Engine

作　　者：许建国 陈赟 张禹 王园丁 Xu Jianguo;Chen Yun;Zhang Yu;Wang Yuanding(Shanghai Institute of Space Propulsion,Shanghai 201112,China;Shanghai Engineering Research Center of Space Engine,Shanghai 201112,China;Academy of Aerospace Propulsion Technology,Xi’an 710100,China)

机构地区：[1]上海空间推进研究所,上海201112 [2]上海空间发动机工程技术研究中心,上海201112 [3]航天推进技术研究院,西安710100

出　　处：《燃烧科学与技术》2025年第2期150-160,共11页Journal of Combustion Science and Technology

基　　金：国家自然科学基金资助项目(U21B2088).

摘　　要：为探究双组元空间发动机内自燃推进剂喷雾、燃烧和传热特性,首先对现有MMH/N_(2)O_(4)(甲基肼/四氧化二氮)详细燃烧反应机理进行适当简化,提出适用于三维模拟的MMH/N_(2)O_(4)化学反应动力学模型,并在不同工况下对简化机理的准确性进行了验证;随后,采用流体体积(volume of fluid,VOF)模型对空间发动机内MMH/N_(2)O_(4)射流撞击雾化过程进行了非稳态模拟,并重点分析了直流互击作用下扇形液膜的形成和演变规律;基于以上化学反应机理及液雾分布模拟结果,在欧拉-拉格朗日体系下构建了离散液滴初始分布,并结合部分搅拌反应器湍流燃烧模型,开展了空间发动机内MMH/N_(2)O_(4)喷雾燃烧及流固耦合传热过程的模拟研究.结果表明,空间发动机内推进剂湍流喷射雾化燃烧过程对壁面冷却液膜的形成和发展具有重要影响,冷却液膜主要出现在燃烧室直线段,在高温燃气与固体域之间建立了一个明显的温度缓冲层,从而实现对发动机壁温的保护.In order to investigate the complex characteristics of spray combustion and conjugate heat transfer proc-esses in bipropellant thrusters,a chemical kinetic model of MMH/N_(2)O_(4)(methylhydrazine/dinitrogen tetroxide)suitable for three-dimensional simulation was first proposed by appropriately simplifying the existing detailed com-bustion reaction mechanism.The accuracy of the proposed reaction mechanism was validated under different condi-tions.A numerical study was then carried out using the VOF(volume of fluid)model to investigate the transient injection and spray processes of MMH/N_(2)O_(4)through a single injection unit in a space engine.The instantaneous formation and evolution processes of the fan-shaped liquid film formed by the impinging jets were analyzed em-phatically.The initial distributions of liquid propellant droplets were calculated on the basis of obtained spray char-acteristic statistics.A numerical study of spray combustion and conjugate heat transfer processes of MMH/N_(2)O_(4)within a space engine was carried out using a combination of the proposed chemical reaction mechanism and the partially stirred reactor combustion model.The results indicate that the spray combustion and conjugate heat trans-fer processes within the space engine are crucial for the formation and development of the liquid film,which pri-marily appears in the combustion chamber to protect the engine wall from erosion.

关 键 词：姿轨控火箭发动机 液体推进剂 雾化燃烧 湍流燃烧模拟 气液两相流 

分 类 号：V231.2[航空宇航科学与技术—航空宇航推进理论与工程]