基于燃面耦合传热的固液发动机内流场模拟方法

Simulation method for hybrid rocket motor based on thermal coupling at burning surface

针对固液火箭发动机中的燃烧流动,建立了一种基于流场与固体燃料之间耦合传热和PDF燃烧模型的通用计算模型。应用该模型计算了二维固液实验发动机燃烧室,得到了燃烧室内部的扩散燃烧和燃面退移速率。计算得到的燃面退移速率与实验结果吻合较好,说明该方法对固液火箭发动机内流场计算有较强的通用性,PDF模型可有效模拟混合发动机中的扩散燃烧过程;简化的一维燃面传热耦合方法可应用到多维计算;该模型可用来模拟固液发动机的内弹道和预示退移速率。

A general calculation model based on thermal coupling at burning face and PDF combustion model was proposed to simulate the flow and combustion in hybrid rocket motor. Two dimensional hybrid rocket motors were simulated by this calculation model and regression rate was obtained.The calculation results agree well with test data,which means the PDF model can simulate the diffusion combustion in hybrid rocket combustor and the simplified one dimensional thermal coupling method at burning surface can be used in multi-dimensional calculations.The calculation model can be widely used in hybrid rocket flowfield simulation and al-so be used to predict the fuel regression rate.