固体火箭发动机点火瞬间火焰传播模型比较研究

Comparison study on ignition transient flame-spreading model of SRM

以N-S方程、k-ε湍流模型、P1辐射模型为基础,采用流固耦合传热的火焰传播边界条件,分别对固体火箭发动机点火瞬间的层流粘性模型、湍流粘性模型、层流粘性辐射模型、湍流粘性辐射模型进行了比较分析研究。以PS-1发动机点火过程为算例的分析表明,燃气和推进剂热力参数相同时,层流粘性模型不能形成火焰;湍流粘性模型虽然形成了燃面,但不可自持燃烧;层流粘性辐射模型的点火诱导期长;湍流粘性辐射模型可正确预示初始发火点和火焰传播过程。

Based on the N-S equation, κ-ε turbulence model and P1 radiation model, four kinds of the models during ignition transient of SRM were compared respectively by using fluid-solid coupling flame-spreading boundary condition, i. e. turbulence viscosity model, laminar viscosity model, laminar viscosity radiation model and turbulence viscosity radiation model. Taking PS-1 motor ignition process as an example, the analysis results show that for laminar viscosity model,the flame can not be formed when thermal parameters of hot gas and propellant are the same;while for turbulence viscosity model, burning surface is formed but self-sustaining combustion can not be made;the ignition induction period of laminar viscosity radiation model is long; turbulence viscosity model can be used for accurately predicting initial ignition point and flame-propagation process.