亚燃燃烧室两相反应流场的燃烧模型  

Combustion models for subsonic two-phase reacting flow in ramjet chamber

作　　者：黄日鑫[1] 谭永华[2] 

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》2008年第2期24-30,共7页Journal of Rocket Propulsion

摘　　要：简要介绍6种可用于亚燃冲压发动机燃烧室计算模型的原理、特点及发展状况;选用两个有代表性的涡耗散概念模型与局部化学平衡模型的计算结果进行分析对比。定量结果显示,基于动力学反应机制的涡耗散概念模型对燃烧室流场的整体描述较好,基于快速反应的局部化学平衡模型会出现燃烧室火焰面前移现象,对于稳定器后方的流场计算结果,二者是一致的。由于考虑的组分较少,涡耗散概念模型计算的温度峰值要高于化学平衡模型的计算结果。两个模型计算的燃烧室室压、喷管出口总温等总体参数均与试验值接近。The principle, features and development status of six combustion models are reviewed. Through a mass of computation experiments by different models, it is found that the main difference between these models in ramjet chamber is the reaction type on which the model based：fast chemistry reaction or finite rate reaction. The simulation results of two typical models （eddy dissipation concept model and Locally chemistry equilibrium model） show that finite rate models are more sophisticated, and fast reaction models may cause early combustion, but are in accord with each other very well once after the flame is held in the chamber. All integer parameters such as chamber static pressure and temperature in nozzle exit of both two models fit the experiment data well.

关 键 词：两相反应 燃烧室 有限速率 EDC PDF 燃烧模型 

分 类 号：TK16[动力工程及工程热物理—热能工程]