点燃式航空重油直喷发动机燃烧系统设计  

Combustion System Design for Spark Ignition Direct Injection Engine with Aviation Heavy Fuel

作　　者：赵振峰[1] 王蕾 俞春存 刘学杰[2] ZHAO Zhenfeng;WANG Lei;YU Chuncun;LIU Xuejie(School of Mechanical Engineering,Beijing Institute of Technology,Beijing 100081,China;College of Foreign Police Affairs,People's Public Security University of China,Beijing 100038,China)

机构地区：[1]北京理工大学机械与车辆学院,北京100081 [2]中国人民公安大学涉外警务学院,北京100038

出　　处：《北京理工大学学报》2024年第2期163-171,共9页Transactions of Beijing Institute of Technology

基　　金：创新特区基金资助项目(21-163-03-ZT-005-01);省级科技重大专项基金资助项目(桂科AA19254036-2)。

摘　　要：为实现航空重油在点燃式二冲程发动机上良好的油气组织和燃烧,采用计算流体动力学(computational fluid dynamics,CFD)仿真的方法针对点燃式二冲程航空重油活塞发动机开展了缸内直喷燃烧系统设计研究,获得了适用于航空重油发动机缸内直喷方式的燃烧室设计方法.通过缸内直喷燃烧室参数化设计,得到了主要结构参数对油气混合过程的影响规律,即燃烧室的偏置距离、半径和深度的变化会影响缸内气流、喷雾和燃烧室壁面三者间的相互作用,从而产生不同的油气混合效果.通过参数正交分析方法,以指示功率和指示比燃油消耗率为评价参数,获得满足性能要求的最佳燃烧室参数组合,结果表明:设计参数为偏置距离8 mm,半径23.5 mm,深度30.2 mm,可使发动机以2.4%的功率损失获得16.9%的经济性改善.To improve fuel/air organization and combustion of spark ignition(SI)two-stroke piston engine with aviation heavy fuel,a direct injection(DI)combustion system was designed and studied based on CFD simula-tion for a SI two-stroke engine,and a combustion chamber design method was obtained suitable for the DI mode of aviation heavy fuel engine.Taking parametric design for the DI combustion chamber,the influence law of the main structural parameters on the fuel/air mixing process was obtained.The results show that variation of the off-set distance,radius and depth of the chamber can affect the interaction among the three parts,cylinder airflow,spray and the chamber wall,so as to produce different fuel/air mixing effects.Through the orthogonal parameter analysis method,taking indicated power and indicated specific fuel consumption rate as evaluation parameters,the optimal combination of chamber parameters was obtained and met the performance requirements.The res-ults show when the parameters set as follow,8 mm offset distance,23.5 mm radius,and 30.2 mm depth,an eco-nomic improvement of 16.9%can be achieved with a power loss of 2.4%only.

关 键 词：点燃式 航空重油 二冲程 缸内直喷 燃烧系统 

分 类 号：TK46[动力工程及工程热物理—动力机械及工程] V234[航空宇航科学与技术—航空宇航推进理论与工程]