FY-2型发动机燃烧室计算模型

A Combustion Modelling of FY-2 Engine

本文提出了一个液体火箭发动机双组元自燃推进剂高压燃烧过程的计算模型。模型考虑了偏二甲肼的分解反应、四氧化二氮的离解反应、高压蒸发、液滴二次雾化以及燃烧室横截面上混合比和流强分布的不均匀性。应用该模型对FY-2型发动机的三种喷注器结构的燃烧效率及能量释放分布进行了理论计算,计算结果与试车数据和现象相当吻合。

A modelling of the high-pressure hypergolic bipropellant combustion process for liquid rocket engine is presented in this paper. The modelling takes account of the decomposition reaction of UDMH, dissociation reaction of N_2O_4, highpressure vaporization, secondary atomization of mixture ratio and flow flux in the cross-section of the combustor. As an example of the application of this model, the combustion efficiency and energy release distribution of 3 injectors for FY-2 Engine are calculated in theory. The calculated results are in good agreement with the experimental data.