高速气流场燃油雾化液滴分布数值研究  

Numerical investigation of spray in high speed airflow

作　　者：马天举[1] 栾希亭[2] 洪流[1] 

机构地区：[1]西安航天动力研究所,陕西西安710100 [2]航天推进技术研究院,陕西西安710100

出　　处：《火箭推进》2009年第3期21-25,共5页Journal of Rocket Propulsion

摘　　要：针对亚燃冲压发动机燃烧室内部流动特点,结合二元稳定器试验台高速气流场燃油雾化特性试验,建立试验件三维模型并对其喷雾两相流动进行数值模拟。主要研究了来流马赫数以及喷嘴条件变化时燃油雾化液滴与油气比的分布。分析认为,来流马赫数的增加使得雾化特征角缩小,可同时改善燃油蒸发并获得更加均匀的油气比分布。随着供油压力的提高,离心式与直流式喷嘴雾化特征角均增大,但供油压力不是影响直流喷嘴雾化锥角的主要因素。计算结果与试验结果对比定性符合良好,定量误差范围可以接受,验证了计算模型与计算方法的正确性,所得到的结果可应用于工程设计。Based on experimental investigation of the liquid fuel atomization in high speed air-flow and the flow characteristics of ramjet combustion chamber, a three-dimensional model was es- tablished. With the two-phase flow numerical simulation, spray field and fuel-air ratio distributions were investigated at different Mach numbers and injector conditions. The simulation results indicate that with the Mach number increasing, an improved vaporization and better fuel distribution were obtained, the atomization angle was reduced. The atomization angles of orifice and swirl injectors were changed with fuel pressure changing, but it was not the main factor. The numerical simulation and the experiment results agreed well. The numerical simulation model method and results can be used in engineering design.

关 键 词：亚燃冲压发动机 燃油雾化 燃料分布 雾化角 数值模拟 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]