固体火箭技术2012，Vol.35Issue(4)：468-473,6.
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
林彬彬 1潘宏亮 1刘洋1
作者信息
- 1. 西北工业大学燃烧、热结构与内流场重点实验室,西安710072
- 折叠
摘要
Abstract
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 three-dimensional N-S equation,particle trajectory model,King's model of boron particles ignition,combustion of boron particles model,and turbulence model as well. Standard k-e model,k-e RNG model,and κ-ω SST two-equation model were applied respectively in the paper. 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 efficiencies 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 afterburner, 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Key words
turbo solid propellant ramjet/ secondary combustion chamber/ boron-based propellant/ numerical simulation/ two phase flow分类
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林彬彬,潘宏亮,刘洋..涡轮增压固体冲压发动机补燃室燃烧数值模拟研究[J].固体火箭技术,2012,35(4):468-473,6.
