涡轮增压固体冲压发动机补燃室燃烧数值模拟研究  

Numerical simulation of the reacting flow field in afterburner of turbo-charged solid propellant ramjet

作　　者：林彬彬[1] 潘宏亮[1] 刘洋[1] 

机构地区：[1]西北工业大学燃烧热结构与内流场重点实验室,西安710072

出　　处：《固体火箭技术》2012年第4期468-473,共6页Journal of Solid Rocket Technology

摘　　要：提出了涡轮增压固体冲压发动机补燃室三股气流燃烧数值模拟的方法。分别采用Standard k-ε、k-εRNG、k-ωSST湍流模型,结合三维N-S方程、颗粒轨道模型、King硼粒子点火模型、硼粒子燃烧模型建立TSPR发动机补燃室三维两相流动燃烧模型。首先,利用本文模型进行冷流掺混分析,确定了试验发动机构型并进行燃烧试验,三股气流形成了稳定燃烧;然后,将数值计算得到的补燃室压强、特征速度、燃烧效率与实验结果进行对比分析,并进行了计算模型可信性分析;文中综合湍流模型对TSPR补燃室燃烧情况模拟的影响,得出硼颗粒模型是进一步提高含硼三股气流模拟精度的主要原因。说明本文采用的模型以及与之相匹配使用的方法适用于TSPR发动机补燃室燃烧情况的分析。采用本文补燃室结构进行试验,有无硼成分的试验燃烧效率分别达到82.1%和88.8%,数值模拟结果显示,还应进一步改进补燃室结构,以降低总压损失,促进补燃室壁面附近的空气参与燃烧,并提高硼粒子燃烧效率。A method to simulate the reacting flows in the afterburner of Turbo charged Solid Propellant Ramjet （TSPR） was proposed. Numerical simulation model of three dimensional two phase flow field of TSPR was established by integrating threedimen sional N-S equation, particle trajectory model, King model of boron particles ignition, combustion of boron particles model, and tur bulence model as well. Standard k-ε model,k-ε RNG model, and k-ω SST two-equation model were applied respectively in the pa per. The configuration of TSPR was based on simulations of cold flow upon various mixing structure and then combustion experiments were carried out. The numerical simulations were validated by comparing the predicted and tested results for static pressure profile a- long the centerline of the secondary combustion chamber,the characteristic velocity of the motor and the combustion efficiency. It is shown that simulations in the paper can be used in the development of TSPR and the numerical model improvements depend mainly on the ignition and burning model of boron particle. The experiments show that the combustion efficieneies are 88.8% for case 1 with boron and 82.1% for case 2 without boron respectively. It is also found out through numerical simulations that the structure of afterburner should be improved further to reduce the loss of the total pressure, promote the combustion near the wall of the afterburn- er, and improve, the combustion efficiency of boron.

关 键 词：涡轮增压固体冲压发动机 补燃室 含硼固体推进剂 数值模拟 两相流 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]